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There has been a need for summarizing and establishing adequate aerodynamic and thermodynamic design criteria for turbojet engine test cells and ground run-up suppressors. These criteria are discussed and their uses are illustrated by examples of typical design problem solutions. The presence of noise suppression structures can have significant influences upon the operation of the turbojet engine. These influences are enumerated and evaluated with recommendations for establishing maximum acceptable effects. Typical test cell configurations are presented and design criteria are established for providing noise suppression facilities which may be utilized for testing a fullize aircraft or an engine by itself. These facilities can be either permanent structures or portable units.

Fourteen firings of the Rocketdyne J-2 rocket engine performed in Test Cell J-4 of the Large Rocket Facility, using modified augmented spark igniter propellant supply lines, are reported herein. These firings were accomplished during test periods J4-1801-39 through J4-1801-41 at pressure altitudes ranging from 88,000 to 109,000 ft at engine start. These were the initial firings at simulated altitude conditions, all related to Saturn V/S-IVB conditions, incorporating engine modifications that were performed as a result of malfunctions that occurred during the flight of vehicle AS-502 on April 4, 1968. Engine start transient evaluations, augmented spark igniter propellant line strain data, engine steady-state and transitory vibration data, and calculated engine steady-state performance data are included. Satisfactory engine operation and augmented spark igniter operation were obtained. The accumulated firing duration was 181.7 sec.

Jet engine being set up for testing with technicians from Propulsion System Laboratory (PSL). Image modified to include photographer taking the photo.

No abstract available

No abstract available

With increasing emphasis on streamlining the acquisition process, ground-test centers like AEDC are re-evaluating their roles in the development of aerospace systems. Instead of the traditional role of merely providing data from ground-test facilities, the new emphasis challenges the Center to become a team member that provides knowledge for risk management and decision making during the development and operation of an aerospace system. As a key link in the transition from a laboratory or design concept to an operational system, the capabilities of a ground-test center can provide a tremendous opportunity to reduce the time and cost involved in flight vehicle system development. AEDC has aggressively accepted the challenge and has developed an Integrated Test and Evaluation (IT&E) approach to support aerospace system development efforts. This paper focuses on an integrated test and evaluation process embraced by AEDC and the USAF Academy in a joint test and analysis effort of the F109 turbofan engine. This process uses a swirl investigation as a vehicle to exercise and demonstrate the approach.

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; bearing housing and shaft during build-up

INCONEL 718 panels after impact testing in the Ballistics Impact Lab with Titanium Simulated Jet Engine Blade

A cooled-gas pyrometer designed for application in a hypersonic research engine program was fabricated and tested. Design and operational considerations and calibration data are presented. The probe was tested in a rocket-engine exhaust stream operating at Mach 2 and 2300 K. Test temperature measurements agreed to within 2 percent with a radiation shielded thermocouple probe.

This thesis explains the design and testing of a water-cooled rotating detonation engine (RDE) run on hydrogen and air. The change in water temperature as it cooled the engine was used to find the steady heat rate into the containing walls of the detonation channel. The engine successfully ran four times for 20 seconds each. The steady-state heat rate was measured to be 2.5% of the propellant lower heating value (LHV) into the outer wall and 7.1% of LHV into the inner wall. Additionally, a quick-response resistance temperature detector (RTD) was used in an uncooled RDE of similar dimension to the cooled RDE to estimate the transient heat flux profile in the detonation channel. The average heat flux into the outer wall near the base of the channel was measured to be four times greater than the average heat flux over the entire cooled wall at steady-state, indicating the heat flux decreases significantly with axial distance. In addition, the large difference in heat absorption between the inner and outer cooled walls indicates that the heat flux into the inner wall is greater than that into the outer wall.

A 1 kW single cylinder free piston Stirling engine, configured as a research engine, was tested with helium working gas. The engine features a posted displacer and dashpot load. The test results show the engine power output and efficiency to be lower than those observed during acceptance tests by the manufacturer. Engine tests results are presented for operation at the two heater head temperatures and with two regenerator porosities, along with flow test results for the heat exchangers.

In order to promote public education and public safety, equal justice for all, a better informed citizenry, the rule of law, world trade and world peace, this legal document is hereby made available on a noncommercial basis, as it is the right of all humans to know and speak the laws that govern them. (For more information: 12 Tables of Code ) Name of Standards Organization: Bureau of Indian Standards (BIS) Division Name: Transport Engineering Section Name: Transport Tractors and Trailers (TED 22) Designator of Legally Binding Document: IS 9099-1 Title of Legally Binding Document: Performance Testing of Powered Industrial Trucks Working in Hazardous Areas, Part I: Internal Combustion Engine Powered Number of Amendments: Equivalence: Superceding: Superceded by: LEGALLY BINDING DOCUMENT Step Out From the Old to the New --Jawaharlal Nehru Invent a new India using knowledge. --Satyanarayan Gangaram Pitroda

INCONEL 718 panels after impact testing in the Ballistics Impact Lab with Titanium Simulated Jet Engine Blade

One of the most important properties of aviation fuels for spark-ignition engines is their knock rating. The CFR engine tests of fuels of 87 octane and above does not always correspond entirely to the actual behavior of these fuels in the airplane engine. A method is therefore developed which, in contrast to the octane number determination, permits a testing of the fuel under various temperatures and fuel mixture conditions. The following reference fuels were employed: 1) Primary fuels; isooctane and n-heptane; 2) Secondary fuels; pure benzene and synthetic benzine.

The Augmented Deflector Exhaust Nozzle (ADEN) exhaust system was tested in the PSL-3 altitude chamber at the NASA Lewis Research Center in order to evaluate aerodynamic performance, cooling-system effectiveness, and mechanical operation at flight-type conditions. The ADEN, a flight-weight, two-dimensional, thrust-vectoring nozzle, was successfully tested on the F404 engine using a remote engine control system for automatic or manual setting of the throat-area control and available fan air for the nozzle internal cooling system. Throughout the test, the ADEN performed with no adverse effects on the engine or augmentor operation.

The performance of a turbocharged rotary engine at power levels above 75 kW (100 hp) was studied. A twin rotor turbocharged Mazda engine was tested at speeds of 3000 to 6000 rpm and boost pressures to 7 psi. The NASA developed combustion diagnostic instrumentation was used to quantify indicated and pumping mean effect pressures, peak pressure, and face to face variability on a cycle by cycle basis. Results of this testing showed that a 5900 rpm a 36 percent increase in power was obtained by operating the engine in the turbocharged configuration. When operating with lean carburetor jets at 105 hp (78.3 kW) and 4000 rpm, a brake specific fuel consumption of 0.45 lbm/lb-hr was measured.

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

As part of the Advanced Lightweight Chamber and Nozzle (ALCAN) program, over 50 hot fire tests were run in the Mojave desert over a wide range of pressures and mixture ratios in February and March. These proof-of-concept engines are designed to perhaps one day produce a booster-sized engine weighing half as much as the SSME, with increased performance. The first round of tests, conducted at Polaris Propulsion's Mojave Test Area, were intended to prove the viability of the concept, according to Rocketdyne's Program Manager Scott Claflin. In other words, we were trying to prove that we could efficiently operate a combustion chamber with a transpiration cooled ceramic matrix composite (CMC) liner Transpiration, a cooling technique in which a very small percentage of the rocket fuel flow is introduced through uniformly distributed pores in the combustion chamber wall, is similar to what happens when humans perspire.

(U) Personnel at the Naval Air Warfare Center Weapons Division (NAWCWD), China Lake, California, in conjunction with Hughes Associates, Inc. (HAI), have been conducting an evaluation for the replacement of Halon 1211 systems on U.S. Navy aircraft carrier flight decks and hangar bays. As such, an effort began in 1996 to provide an overall assessment. This endeavor entailed four phases: (1) an alternative development status, (2) a requirements review, (3) a mission critical reserve evaluation, and (4) a replacement program plan. The effort described herein pertains to the fourth stage. (U) To evaluate potential Halon 1211 replacement systems for flight deck use, a program was established to identify the threats from engine fires and determine suitable alternatives. A systems engineering approach was adopted in which understanding the fire threats and extinguishing requirements before recommending a replacement for Halon 1211 in naval aviation applications was critical. This approach required the use of a realistic test scenario that adequately simulated the small two- and three-dimensional engine and fires encountered in the field. This program focused on internal engine and nacelle fires. (U) This report provides a summary of the work completed for the internal engine and the nacelle fire series, a description of this testing, and a discussion of the results. Also included are the authors' conclusions and recommendations, as well as the future direction for the program.

Techniques for ground-testing of ion engines are reviewed. Procedures for the neutralization of ion beams and the results of experiments measuring the space charge and current neutrality achieved are presented. Results of experiments with the window probe and a new probe for the measurement of beam potential are also presented. Results achieved with the methods described in the first Technical Documentary Report are discussed; more recently developed methods and their results are also reviewed.

This report details the use of infrared imaging for temperature measurement and thermal pattern determination during simulated altitude engine testing in the NASA Lewis Propulsion Systems Laboratory. Three identical argon-cooled imaging systems were installed in the facility exhaust collector behind sapphire windows to look at engine internal surfaces. The report describes the components of each system, presents the specifics of the complicated installation, and explains the operation of the systems during engine testing. During the program, several problems emerged, such as argon contamination system, component overheating, cracked sapphire windows, and other unexplained effects. This report includes a summary of the difficulties as well as the solutions developed. The systems performed well, considering they were in an unusually harsh exhaust environment. Both video and digital data were recorded, and the information provided valuable material for the engineers and designers to quickly make any necessary design changes to the engine hardware cooling system. The knowledge and experience gained during this program greatly simplified the installation and use of the systems during later test programs in the facility. The infrared imaging systems have significantly enhanced the measurement capabilities of the facility, and have become an outstanding and versatile testing resource in the Propulsion Systems Laboratory.

Five idle-mode firings of the Rocketdyne J-2S rocket engine (S/N J- 112-1A) were conducted in Test Cell J-4 of the Large Rocket Facility on April 17 and 24, 1969. These firings were accomplished at pressure altitudes of approximately 100,000 ft at engine start. The objectives were: (1) to investigate engine idle-mode operating characteristics with a redesigned injector (oxidizer idle-mode compartment consisted of the injector posts in the tenth row from the center of the injector); (2) to determine fuel injection density for varying pump inlet pressures; and (3) to determine engine idle-mode performance. The lowest injection density was 0.055 lbm/cu. ft. with the thrust chamber bypass valve closed. Engine average characteristic velocity for this injector configuration was about 2.6 percent greater than that recorded during tests with the previous injector.

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

Document number CIA-RDP82-00457R003000650010-0 declassified and released through the CIA's CREST database. Previously available only on four computers located outside of Washington D.C., the Agency was successfully pressured into putting the files online as a result of a MuckRock lawsuit and the efforts of Emma Best. The metadata was collected by Data.World, and the files are now being archived and made text searchable by the Internet Archive.

Modifications were made to NAPTC altitude chamber 3E to provide the capability to test current V/STOL aircraft engines. A test program was conducted with a F402 vectored-thrust turbofan engine to evaluate the modifications and verify facility operational capability. (Author)

The test program and report were conducted and prepared by the U.S. Army Tank-Automotive Command Propulsion Systems Division and laboratory. The report details performance and durability tests using Fire Resistant Diesel Fuel (FRDF). The objective of the FRDF program is to develop a future fuel that will reduce the vulnerability of military vehicles to fire, decrease the number of vehicles lost and repair costs, and increase crew survivability. The objective of this project is to evaluate the performance and endurance of a medium-sized, unmodified commercial production diesel engine of 200-hp range tested with FRDF. The FRDF contains tap water of 10.2 to 13.2 percent volume. Another objective of this project is to inspect the fuel-wetted parts of the fuel injection system and engine, and determine the effect of the water in the fuel on these parts.

Five firings of the Rocketdyne J-2 rocket engine (S/N J-2047) were conducted in Test Cell J-4 of the Large Rocket Facility. These firings were accomplished during test period J4-1801-16 at pressure altitudes of approximately 100,000 ft at engine start to investigate S-II/S-V (1) fuel pump operation during the start transient at lower than minimum model specification inlet pressure, (2) thrust chamber pressure buildup rate with low starting energy, and (3) gas generator and augmented spark igniter temperature transients with warmest and coldest expected thrust chamber temperatures as predicted from the AS-501 countdown demonstration. Engine operation was satisfactory for all firings. The accumulated firing duration was 46.2 sec.

Eleven firings of the Rocketdyne J-2S rocket engine were conducted. These firings were accomplished at pressure altitudes ranging from 80,000 to 108,000 ft at engine start signal. The major objectives for these tests were to verify stable idle-mode operation, confirm that oxidizer injection temperatures were not excessive during transition from main-stage to post-main-stage idle- mode operation, evaluate main-stage performance, and determine the rate at which thrust chamber temperature increased during pre-main-stage idle mode. A full- face oxidizer flow injector configuration was utilized during this series of tests for the distribution of oxidizer during idle-mode operation. Brief durations (20 sec) of stable idle-mode operation (chamber pressure oscillations + or - psi) were achieved. Oxidizer injection temperatures exhibited only insignificant increases (10F) during transition to post-main-stage idle-mode operation. The maximum rate at which the thrust chamber temperature increased during idle-mode operation with high oxidizer (45-psia) and low fuel (27-psia) pump inlet conditions with 6F/sec. Three firings which simulated orbital restart conditions were prematurely terminated during transition to main stage by the vibration safety cutoff system. Liquid fuel was present at the injector at the dome prime when the excessive vibrations were first recorded.

Five firings of the Rocketdyne J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The firings were accomplished during test period J4-1801-23 at pressure altitudes ranging from 105,500 to 113,000 ft at engine start to evaluate the effects of predicted Saturn S-II stage pre-fire conditions on J-2 engine start transients. Engine components were thermally conditioned to simulate the expected S-II interstage/engine thermal environment. Satisfactory engine operation was obtained. Accumulated firing duration was 56.3 sec.

Tests were conducted at the FAA Air Blast Test Facility during which Halon 1202 or Halon 1301 was discharged into the nacelle of an F/EF-111 test article through the aircraft's on-board agent distribution system. Various ground/flight conditions were simulated by providing controlled nacelle ventilating flows using by-pass air from a YTF-33 engine. Preliminary test indicated that some advantage resulted using the more volatile Halon 1301 agent. Tests also revealed that using either agent, the current on-board nacelle fire extinguishing system does not meet the recommended minimum requirements for an acceptable system in a major portion of the aircrafts operational flight envelope. And finally, the test results indicate that a revision to Mil-E-22285 should be considered. Keywords: Fire extinguishing agents; Fire protection.

A test was conducted by the Air Force Aero Propulsion Laboratory to study the performance of jet engine compressors during engine speed transients. Effective analysis of the test results required accurate, high speed data acquisition during the transients. On-line reduction and display of the performance data was desirable to improve the efficiency of the test operations. This paper describes the software that was designed and implemented to acquire and display the performance data. The software controls data acquisition and calibration equipment, provides on-line calibration of transducers, records the data, reduces and displays performance data (including graphics), and allows the test operator to control these functions. (Author)

The Corps of Engineers (CE) Test Procedures document has been prepared in a format similar to the referenced MIL-STD-705B test methods to provide for easy implementation by CE district and division personnel. The procedures provide for acceptance testing large diesel engine-generator sets--up to 6000 kW capacity range--intended for installation in fixed military facilities as Class A (Prime), Class B (Standby), or Class C (Emergency) electrical power generation sources. This document provides a list of MIL-STD-705B test methods which are directly applicable for acceptance testing large diesel engine-generator sets. In addition, the document provides new test procedures numbered CE-TP-1001 through 1004, designed specifically for acceptance testing large stationary diesel engine-generator sets intended for electrical power generation within fixed military facilities. (Author)

Introduction In Asia, two-wheeled agricultural tractors predominantly use single-cylinder two-stroke diesel engines, which are characterized by high fuel consumption and substantial air pollution. At the same time, the severe environmental impacts of energy production from diminishing fossil fuel reserves are increasingly evident. Therefore, it is essential to develop sustainable and clean energy sources to meet these needs. Biodiesel is an alternative fuel that can be blended with conventional diesel to help reduce environmental pollution. In this study, diesel-biodiesel blends produced from rapeseed, soybean, and palm oil were evaluated for their effects on engine performance metrics, including power (P), torque (T), and specific fuel consumption (SFC). Furthermore, the emissions of pollutants (NOx, HC, CO, and CO₂) from these fuels were measured and modeled using linear and non-linear regression, as well as the adaptive neuro-fuzzy inference system (ANFIS). Materials and Methods To leverage the benefits of palm oil biodiesel, known for its high calorific value, along with the low kinematic viscosity of biodiesel derived from soybean and rapeseed oils, pure diesel was blended with 10% and 20% mixtures of rapeseed, soybean, and palm biodiesel, as well as 10% and 20% combinations of all three biodiesels. These nine fuel blends were tested at four engine speeds (1800, 2100, 2400, and 2700 rpm) under full load conditions. The diesel-biodiesel blends were produced at Sari Agricultural Sciences and Natural Resources University (SANRU) and transported to the engine laboratory at Tarbiat Modares University in Tehran, Iran, for detailed analysis. A total of 36 treatments were evaluated using a randomized complete block design (RCBD), incorporating four engine speeds and nine fuel types. The measured outputs included engine power, torque, specific fuel consumption, and pollutant emissions such as NOx, HC, CO, and CO₂. The collected data were used as input for modeling through both linear and non-linear regression in SPSS software, as well as ANFIS in MATLAB software. Results and Discussion This study evaluated nine diesel-biodiesel blends derived from palm, rapeseed, and soybean oils using a diesel engine in a controlled laboratory setting. Tests were carried out at four engine speeds—1800, 2100, 2400, and 2700 rpm—under full load conditions to assess engine performance and exhaust emissions. The results showed that for all tested fuel blends, power, specific fuel consumption, and pollutant emissions increased with engine speed, while torque decreased. Based on the findings, a blend containing 20% palm biodiesel can be used as an alternative fuel in diesel engines without requiring any modifications. The modeling results indicated that non-linear regression provided better accuracy than linear regression. However, ANFIS demonstrated a much higher correlation between actual and predicted values, with R² exceeding 0.98 for both performance parameters and emissions, compared to R² values below 0.47 for linear regression and below 0.92 for non-linear regression. The ANFIS model achieved its highest and lowest R² values at 0.99 for specific fuel consumption (SFC) and 0.98 for power (P), respectively; substantially higher than those from linear regression, which yielded 0.47 for torque (T) and 0.00 for power. Non-linear regression resulted in R² values of 0.92 for SFC and 0.60 for carbon monoxide (CO), still lower than those achieved by ANFIS. Overall, the highest R² value recorded was 0.7525 for torque, and the lowest was 0.6112 for power. Conclusion Single-cylinder diesel engines, which have high fuel consumption and contribute to air pollution, are commonly used in two-wheel agricultural tractors across Asia. One approach to reducing the environmental impact of fossil fuels is to use biodiesel in these engines without requiring any modifications. The results of this study showed that a 20% blend of palm biodiesel can be an effective alternative fuel for diesel engines, with no need for engine modification. Furthermore, the modeling results indicated a significantly higher correlation (R² > 0.98) between actual and predicted values of performance variables and emissions using ANFIS, compared to linear regression (R² < 0.47) and non-linear regression (R² < 0.92). Therefore, ANFIS can be effectively used to accurately predict engine performance and emission parameters.

Introduction In Asia, two-wheeled agricultural tractors predominantly use single-cylinder two-stroke diesel engines, which are characterized by high fuel consumption and substantial air pollution. At the same time, the severe environmental impacts of energy production from diminishing fossil fuel reserves are increasingly evident. Therefore, it is essential to develop sustainable and clean energy sources to meet these needs. Biodiesel is an alternative fuel that can be blended with conventional diesel to help reduce environmental pollution. In this study, diesel-biodiesel blends produced from rapeseed, soybean, and palm oil were evaluated for their effects on engine performance metrics, including power (P), torque (T), and specific fuel consumption (SFC). Furthermore, the emissions of pollutants (NOx, HC, CO, and CO₂) from these fuels were measured and modeled using linear and non-linear regression, as well as the adaptive neuro-fuzzy inference system (ANFIS). Materials and Methods To leverage the benefits of palm oil biodiesel, known for its high calorific value, along with the low kinematic viscosity of biodiesel derived from soybean and rapeseed oils, pure diesel was blended with 10% and 20% mixtures of rapeseed, soybean, and palm biodiesel, as well as 10% and 20% combinations of all three biodiesels. These nine fuel blends were tested at four engine speeds (1800, 2100, 2400, and 2700 rpm) under full load conditions. The diesel-biodiesel blends were produced at Sari Agricultural Sciences and Natural Resources University (SANRU) and transported to the engine laboratory at Tarbiat Modares University in Tehran, Iran, for detailed analysis. A total of 36 treatments were evaluated using a randomized complete block design (RCBD), incorporating four engine speeds and nine fuel types. The measured outputs included engine power, torque, specific fuel consumption, and pollutant emissions such as NOx, HC, CO, and CO₂. The collected data were used as input for modeling through both linear and non-linear regression in SPSS software, as well as ANFIS in MATLAB software. Results and Discussion This study evaluated nine diesel-biodiesel blends derived from palm, rapeseed, and soybean oils using a diesel engine in a controlled laboratory setting. Tests were carried out at four engine speeds—1800, 2100, 2400, and 2700 rpm—under full load conditions to assess engine performance and exhaust emissions. The results showed that for all tested fuel blends, power, specific fuel consumption, and pollutant emissions increased with engine speed, while torque decreased. Based on the findings, a blend containing 20% palm biodiesel can be used as an alternative fuel in diesel engines without requiring any modifications. The modeling results indicated that non-linear regression provided better accuracy than linear regression. However, ANFIS demonstrated a much higher correlation between actual and predicted values, with R² exceeding 0.98 for both performance parameters and emissions, compared to R² values below 0.47 for linear regression and below 0.92 for non-linear regression. The ANFIS model achieved its highest and lowest R² values at 0.99 for specific fuel consumption (SFC) and 0.98 for power (P), respectively; substantially higher than those from linear regression, which yielded 0.47 for torque (T) and 0.00 for power. Non-linear regression resulted in R² values of 0.92 for SFC and 0.60 for carbon monoxide (CO), still lower than those achieved by ANFIS. Overall, the highest R² value recorded was 0.7525 for torque, and the lowest was 0.6112 for power. Conclusion Single-cylinder diesel engines, which have high fuel consumption and contribute to air pollution, are commonly used in two-wheel agricultural tractors across Asia. One approach to reducing the environmental impact of fossil fuels is to use biodiesel in these engines without requiring any modifications. The results of this study showed that a 20% blend of palm biodiesel can be an effective alternative fuel for diesel engines, with no need for engine modification. Furthermore, the modeling results indicated a significantly higher correlation (R² > 0.98) between actual and predicted values of performance variables and emissions using ANFIS, compared to linear regression (R² < 0.47) and non-linear regression (R² < 0.92). Therefore, ANFIS can be effectively used to accurately predict engine performance and emission parameters.

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; oil and air lines plus instrumentation between collector and gearbox

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; close up - throttle valve -wide open; oil and air lines plus instrumentation between collector and gearbox.

The combustion stability characteristics of engines applicable to the Space Shuttle Orbit Maneuvering System and the adequacy of acoustic cavities as a means of assuring stability in these engines were investigated. The study comprised full-scale stability rating tests, bench-scale acoustic model tests and analysis. Two series of stability rating tests were made. Acoustic model tests were made to determine the resonance characteristics and effects of acoustic cavities. Analytical studies were done to aid design of the cavity configurations to be tested and, also, to aid evaluation of the effectiveness of acoustic cavities from available test results.

In a partnership between the NASA Glenn Research Center and Pratt & Whitney, a ceramic heat exchanger panel intended for use along the hot-flow-path walls of future reusable launch vehicles was designed, fabricated, and tested. These regeneratively cooled ceramic matrix composite (CMC) panels offer lighter weight, higher operating temperatures, and reduced coolant requirements in comparison to their more traditional metallic counterparts. A maintainable approach to the design was adopted which allowed the panel components to be assembled with high-temperature fasteners rather than by permanent bonding methods. With this approach, the CMC hot face sheet, the coolant containment system, and backside structure were all fabricated separately and could be replaced individually as the need occurred during use. This maintainable design leads to both ease of fabrication and reduced cost.

A screening program to determine the effects of high pressure hydrogen on selected candidate materials for advanced single crystal turbine blade applications is examined. The alloys chosen for the investigation are CM SX-2, CM SX-4C, Rene N-4, and PWA1480. Testing is carried out in hydrogen and helium at 34 MPa and room temperature, with both notched and unnotched single crystal specimens. Results show a significant variation in susceptibility to Hydrogen Environment Embrittlement (HEE) among the four alloys and a marked difference in fracture topography between hydrogen and helium environment specimens.

A screening program to determine the effects of high pressure hydrogen on selected candidate materials for advanced single crystal turbine blade applications is examined. The alloys chosen for the investigation are CM SX-2, CM SX-4C, Rene N-4, and PWA1480. Testing is carried out in hydrogen and helium at 34 MPa and room temperature, with both notched and unnotched single crystal specimens. Results show a significant variation in susceptibility to Hydrogen Environment Embrittlement (HEE) among the four alloys and a marked difference in fracture topography between hydrogen and helium environment specimens.

Fourteen firings of the Rocketdyne J-2S rocket engine (S/N J-115) were conducted during test periods J4-1001-16 through -20 between March 10 and May 19, 1970. The major objectives of these tests were: (1) development of a throttling capability using a variable-position tapoff valve for thrust control; (2) demonstration of satisfactory idle-mode operation (both pre- and post-main stage) over a wide range of fuel and oxidizer pump inlet pressures; (3) determine the suitability of the S-IVB propellant recirculation system to prefire condition propellants and prechill engine propellant pumps; and (4) determine steady-state engine performance during main-stage operation. All major objectives were satisfactorily accomplished.

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

A study is presented on the relationship between a pre-detonator and a detonation channel of an RDE. Testing was conducted on a straight narrow channel made of clear polycarbonate windows connected to an H2/O2 pre-detonator to simulate the RDE initiation scheme and allow for flow visualization. A comparison is made on decoupling distance and wave velocities for a range of pre-detonator designs, inclination angles, equivalence ratios and geometries placed within the simulated channel. Regardless of inclination angle or equivalence ratio the detonation wave decoupled within 25 mm from the pre-detonator exit into the channel. A step change in diameter 25 mm from the exit of the pre-detonator increased the coupled distance to approximately 40 mm from the pre-detonator exit. A step diameter change also increased the exit velocity of the wave and directionalized the flow. Wedges of 30 , 45 and 60 , placed in the channel next to the pre-detonator exit, increased the distance the shock and flame remained coupled from the pre-detonator exit to 42 mm, 50 mm and 60 mm, respectively.

The main objective of this investigation is to assess the influence of different types and magnitudes of swirl on the performance and compatibility of turbojet engines. The generation of intake swirl, typical for many supersonic combat aircraft, is described. Essentially two basic types, i.e. twin swirl and bulk swirl of varying strength and also combinations thereof, have been selected in order to simulate these swirl patterns by subscale swirl generators in a model wind tunnel. The swirl patterns measured behind these generators show good agreement with the target patterns selected at the beginning. The small scale swirl generators are being rebuilt at full scale for subsequent testing in front of a Larzac engine under static conditions with a bellmouth inlet at the engine test facility of the Jet Propulsion Instituet at the Universitaet der Dundeswehr Muenchen.

Engineers at the Marshall Space Flight Center install the F-1 engines on the S-IC stage thrust structure at the S-IC static test stand. Engines are installed on the stage after it has been placed in the test stand. Five F-1 engines, each weighing 10 tons, gave the booster a total thrust of 7,500,000 pounds, roughly equivalent to 160 million horsepower.

Contents include the following: Objectives and motivation for testing. Technology, Research and Development Test and Evaluation (RDT&E), evolutionary. Representative Liquid Rocket Engine (LRE) test compaigns. Apollo, shuttle, Expandable Launch Vehicles (ELV) propulsion. Overview of test facilities for liquid rocket engines. Boost, upper stage (sea-level and altitude). Statistics (historical) of Liquid Rocket Engine Testing. LOX/LH, LOX/RP, other development. Test project enablers: engineering tools, operations, processes, infrastructure.

Repeated and catastrophic piston failures in a group of large diesel engines deployed in Vietnam for power generation purposes, revealed the urgent need for the development of a fast, reliable means for the detection of incipient failures in these engines. As a result of work subsequently performed by the ROICC-Pacific and various agencies and consultants under his direction, a very successful nondestructive testing technique was established. This technique utilized commercial ultrasonic instrumentation of the pulse-echo type. The procedure, as finalized, will unfailingly detect cracks in the major webs of the diesel engine pistons under consideration, and requires only the removal of the cylinder head for access to the piston top. The only major constraints in the application of this technique are the requirements that the piston material be homogeneous, detailed information relating to piston configuration be available, and the diagnosis be made by technical personnel experiences in ultrasonic interpretation.

Five nonfiring propellant pump performance tests of the J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. The tests were accomplished during test period J4-1801-10 at pressure altitudes of approximately 100,000 ft to evaluate the effects of low fuel pump inlet pressure on pump operating characteristics (tests 10A through 10D) and to determine the effects of spinup with dry pumps on test 10E. In the first four tests, liquid nitrogen was utilized as the operating fluid in the oxidizer system for safety reasons and to prevent engine firing on any test. Thrust chamber and turbine components were thermally conditioned before each performance test.