A normal shock was positioned at distances ranging from 0.4 to 2.0 annulus gaps upstream from the diffuser entrance; the corresponding shock Mach number ranged from 1.40 to 1.47. Boundary layer suction flows as high as about 13 percent of the diffuser entrance flow were employed. The equivalent conical expansion angle of the diffuser was 10 degrees with about 5-percent suction flow, the over-all total pressure loss of the 10 degrees diffuser was less than that for a 5 degrees diffuser with no...
Topics: DTIC Archive, SHOEMAKER, CHARLES J, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
The USN T-2C is a trainer aircraft powered by two J85-GE-4A turbojet engines. This report provides far-field measured and extrapolated data defining both physical and psychoacoustic measures of the bioacoustic environments produced by this aircraft operating on a ground runup pad for two engine/power conditions. Far-field data measured at 16 locations are normalized to standard meteorological conditions and extrapolated from 75-8000 meters to derive sets of equal-value contours as a function of...
Topics: DTIC Archive, Powell,Robert G, AEROSPACE MEDICAL RESEARCH LAB WRIGHT-PATTERSON AFB OHIO, *NOISE...
411
411
Jun 17, 2010
06/10
by
Kaufman, W. B.; Lord, A. M
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Investigation on size and density of boric oxide exhaust cloud of turbojet engine operating on trimethylborate fuel
Topics: BORATES, BORON OXIDES, CLOUDS, EXHAUST GASES, TURBOJET ENGINES, BORIC OXIDE, EXHAUST GAS, TURBOJET...
761
761
Jul 9, 2010
07/10
by
SEIFERTH, R. W
texts
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ABLATOR HEAT SHIELD CONFIGURATION OPTIMIZATION STUDIES WERE CONDUCTED FOR THE ORBITER. ABLATOR AND RSI TRAJECTORIES FOR DESIGN STUDIES WERE SHAPED TO TAKE ADVANTAGE OF THE LOW CONDUCTANCE OF CERAMIC RSI AND HIGH TEMPERATURE CAPABILITY OF ABLATORS. COMPARATIVE WEIGHTS WERE ESTABLISHED FOR THE RSI SYSTEM AND FOR DIRECT BOND AND MECHANICALLY ATTACHED ABLATOR SYSTEMS. ABLATOR SYSTEM COSTS WERE DETERMINED FOR FABRICATION, INSTALLATION AND REFURBISHMENT. COST PENALTIES WERE ASSIGNED FOR PAYLOAD...
Topics: RADIATIVE HEAT TRANSFER, TURBOJET ENGINES, COMBUSTION CHAMBERS, FLAME PROPAGATION
843
843
Jul 11, 2010
07/10
by
Jones, R. T
texts
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The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are...
Topics: FILM COOLING, HEAT TRANSFER COEFFICIENTS, PLUG NOZZLES, EXHAUST NOZZLES, J-85 ENGINE, SUPERSONIC...
306
306
Jul 26, 2010
07/10
by
Carden, Huey D.; Robinson, Martha P
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Failure behavior results are presented from crash dynamics research using concepts of aircraft elements and substructure not necessarily designed or optimized for energy absorption or crash loading considerations. To achieve desired new designs incorporating improved energy absorption capabilities often requires an understanding of how more conventional designs behave under crash loadings. Experimental and analytical data are presented which indicate some general trends in the failure behavior...
Topics: AERODYNAMIC CONFIGURATIONS, SONIC BOOMS, THERMAL PROTECTION, TURBOJET ENGINES, AIRCRAFT...
132
132
May 27, 2011
05/11
by
Newton, Elizabet
texts
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The research performed under this contract is part of an on-going investigation to explore the finest time-resolution hard X-ray data available on solar flares. Since 1991, the Burst and Transient Source Experiment (BATSE) aboard the Compton Gamma Ray Observatory has provided almost continual monitoring of the Sun in the hard X-ray and gamma-ray region of the spectrum. BATSE provides for the first time a temporal resolution in the data comparable to the timescales on which flare particle...
Topics: ENGINE FAILURE, RELIABILITY, TURBOJET ENGINES, THEORIES, EXPERIMENTATION
231
231
Jun 1, 2011
06/11
by
Huber, Paul W
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Preliminary tests have been made of a small burner to meet the requirements for application to supersonic ram jets. The principal requirements were taken as: (1) efficient combustion in a high-velocity air stream, (2) utilization for combustion of only a small fraction of the air passing through the unit, (3) low resistance to air flow, (4) simple construction, and (5) light weight. Tests of a small burner were carried to stream velocities of nearly 150 feet per second and fuel rates such that...
Topics: WIND TUNNEL TESTS, AERODYNAMIC CONFIGURATIONS, COMPRESSORS, AERODYNAMIC CHARACTERISTICS, AXIAL FLOW...
Experimental transient turbine blade temperatures were obtained from tests conducted on air-cooled blades in a research turbojet engine, cycling between cruise and idle conditions. Transient data were recorded by a high speed data acquisition system. Temperatures at the same phase of each transient cycle were repeatable between cycles to within 3.9 K (7 F). Turbine inlet pressures were repeatable between cycles to within 0.32 N/sq cm (0.47 psia). The tests were conducted at a gas stream...
Topics: NASA Technical Reports Server (NTRS), TURBINE BLADES, TURBOJET ENGINES, AIR COOLING, GAS STREAMS,...
Six of the candidate propulsion systems for the High-Speed Civil Transport are the turbojet, turbine bypass engine, mixed flow turbofan, variable cycle engine, Flade engine, and the inverting flow valve engine. A comparison of these propulsion systems by NASA's Glenn Research Center, paralleling studies within the aircraft industry, is presented. This report describes the Glenn Aeropropulsion Analysis Office's contribution to the High-Speed Research Program's 1993 and 1994 propulsion system...
Topics: NASA Technical Reports Server (NTRS), PROPULSION SYSTEM CONFIGURATIONS, SUPERSONIC AIRCRAFT,...
The computer program described calculates the design-point characteristics of a gas generator or a turbojet lift engine for V/STOL applications. The program computes the dimensions and mass, as well as the thermodynamic performance of the model engine and its components. The program was written in FORTRAN 4 language. Provision has been made so that the program accepts input values in either SI Units or U.S. Customary Units. Each engine design-point calculation requires less than 0.5 second of...
Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMS, ENGINE DESIGN, PROPULSION SYSTEM...
678
678
May 27, 2011
05/11
by
NON
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The growth in cost and importance of software to NASA has caused NASA to address the improvement of software development across the agency. One of the products of this program is a series of guidebooks that define a NASA concept of the assurance processes that are used in software development. The Software Assurance Guidebook, NASA-GB-A201, issued in September, 1989, provides an overall picture of the NASA concepts and practices in software assurance. Second level guidebooks focus on specific...
Topics: TURBOJET ENGINES, COBALT ALLOYS, DUCTILITY, FRACTURES (MATERIALS), THERMAL RESISTANCE, ENGINE...
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342
May 27, 2011
05/11
by
NON
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PRESENTED IS A COLLECTION OF ARTICLES IN THREE SECTIONS. THE FIRST SECTION DESCRIBES SINGLE-MODEL AUTOMATIC COUNTER INSTALLATIONS USED TO MEASURE THE FREQUENCY OF EXTENSIVE ATMOSPHERIC SHOWERS AND COSMIC RAYS BELOW GROUND AND APPARATUS WHICH RECORD THE INTENSITY ABOARD ARTIFICIAL EARTH SATELLITES. THE SECOND SECTION DEALS WITH ANALYSIS OF THE ROLE PLAYED BY METEOROLOGICAL FACTORS IN COSMIC-RAY VARIATIONS. THE THIRD SECTION DESCRIBES EXPERIMENTAL AND THEORETICAL INVESTIGATIONS OF...
Topics: WIND TUNNEL TESTS, AFTERBURNING, ANGLE OF ATTACK, ENGINE DESIGN, FLIGHT CONDITIONS, FUSELAGES, JET...
393
393
May 6, 2010
05/10
by
Childs, J. H.; Norgren, C. T
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Effect of fuel injector and liner design on performance of turbojet combustor with vapor fuel
Topics: ANNULI, COMBUSTOR, FUEL INJECTION, LINER, ATOMIZERS, COMBUSTION CHAMBERS, FUEL INJECTION,...
466
466
May 6, 2010
05/10
by
Boksenbom, A. S.; Heppler, H.; Novik, D
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No Abstract Available
Topics: ENGINE CONTROL, FEEDBACK CONTROL, LINEAR SYSTEMS, OPTIMIZATION, SERVOMECHANISMS, TURBOJET ENGINES
1,171
1.2K
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Geodetic information is presented for NASA tracking stations and observation stations in the NASA geodetic satellites program. A geodetic data sheet is provided for each station, giving the position of the station and describing briefly how it was established. Geodetic positions and geocentric coordinates of these stations are tabulated on local or major geodetic datums, and on selected world geodetic systems when available information permits.
Topics: JET AIRCRAFT NOISE, REFLECTION, SOUND PRESSURE, TURBOJET ENGINES, ACOUSTIC MEASUREMENT, SOUND...
384
384
Jul 11, 2010
07/10
by
Davis, D. D
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The technique of flash photolysis-resonance fluorescence was utilized to study nine reactions of stratospheric importance. The tropospheric degradation reactions of seven halogenated hydrocarbons were studied to assess their possible influx into the stratosphere. There are reactions of either Cl, OH, or O(3P) species with hydrogenated species, O3 or chlorinated compounds. Apart from the kinetic measurements, the quantum yield for the production of O(1D) from O3 in the crucial wavelength region...
Topics: DATA ACQUISITION, MICROPROCESSORS, OPTICAL MEMORY (DATA STORAGE), STRUCTURAL VIBRATION, SYSTEMS...
365
365
Jul 11, 2010
07/10
by
Isenberg, J. M.; Southall, J. W
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The Integrated Programs for Aerospace Vehicle Design (IPAD) is a computing system to support company-wide design information processing. This document presents a brief description of the management system used to direct and control a product-oriented program. This document, together with the reference design process (CR 2981) and the manufacture interactions with the design process (CR 2982), comprises the reference information that forms the basis for specifying IPAD system requirements.
Topics: ENGINE DESIGN, RECONNAISSANCE AIRCRAFT, TURBOJET ENGINES, TURBOROCKET ENGINES, U-2 AIRCRAFT, HIGH...
310
310
Jun 1, 2011
06/11
by
Kerslake, Thomas W
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This presentation reviews Solar Electric Propulsion (SEP) Mission Architectures with a slant towards power system technologies and challenges. The low-mass, high-performance attributes of SEP systems have attracted spacecraft designers and mission planners alike and have led to a myriad of proposed Earth orbiting and planetary exploration missions. These SEP missions are discussed from the earliest missions in the 1960's, to first demonstrate electric thrusters, to the multi-megawatt missions...
Topics: CENTRIFUGAL COMPRESSORS, FLOW EQUATIONS, FAILURE ANALYSIS, PRESSURE RATIO, WIND TUNNEL APPARATUS,...
189
189
Jun 1, 2011
06/11
by
Alexander, Sidney R.; Katz, Elli
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Flight tests were conducted to determine the effect of length of a conical windshield on the drag of a bluff body moving at supersonic speeds. A comparison is made between results obtained and results of previous drag tests of body-windshield combinations.The effect of increasing the length of the windshield is discussed.
Topics: TURBOJET ENGINES, ALTITUDE SIMULATION, SPRAY NOZZLES, TURBINE BLADES, SIMULATION, TURBOCOMPRESSORS,...
149
149
Jun 2, 2011
06/11
by
Heymsfield, Andrew J.; Schmitt, Carl G.; Bansemer, Aaron; Baumgardner, Darrel; Weinstock, Elliot M.; Smith, Jessic
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This study derives effective ice particle densities from data collected from the NASA WB-57F aircraft near the tops of anvils during the Cirrus Regional Study of Tropical Anvils and Cirrus Layers (CRYSTAL) Florida Area Cirrus Experiment (FACE) in southern Florida in July 2002. The effective density, defined as the ice particle mass divided by the volume of an equivalent diameter liquid sphere, is obtained for particle populations and single sizes containing mixed particle habits using...
Topics: AEROACOUSTICS, CONICS, NOISE REDUCTION, AIRCRAFT NOISE, AERODYNAMIC NOISE, TURBOJET ENGINES, FLIGHT...
This report covers work carried out at AFAPL's Turbo Structures Research Laboratory (TSRL) on the transient structural response of an isotropic cantilevered plate subjected to normal impact by a ballistic pendulum. The program was a combined experimental/analytical effort. The experimental portion utilized a pulsed ruby laser to obtain holographic interferograms of the plate's deformation following impact. The analytical portion of the work consisted of mathematically modelling the plate using...
Topics: DTIC Archive, MacBain,James C, AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO, *IMPACT,...
Preliminary data from an experimental combustor show that the NOx emission index, g(NO2)/Kg fuel, is about three times greater for hydrogen than for JP at simulated cruise conditions. However, if these results are applied to aircraft designed for a given mission, hydrogen's higher heating value enables the aircraft to have a lower gross weight and a lower fuel flow rate so that the NOx emission rate, Kg (NO2)/hr may be reduced about 30 percent compared to JP. Theoretical kinetics calculations...
Topics: NASA Technical Reports Server (NTRS), COMBUSTION PRODUCTS, EXHAUST GASES, JET ENGINE FUELS,...
Evaluations were made of (1) YJ engine component improvements, (2) J engines in the production configuration being delivered in the first operational T-38 aircraft, and (3) a modified production J engine (General Electric Operation Nutcracker.
Topics: DTIC Archive, Hobbs, Thomas H, AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA, *TURBOJET ENGINES,...
The integrity and performance of brush seals have been established. Severe bench and engine tests have shown high initial wear or run-in rates, material smearing at the interface, and bristle and rub-runner wear, but the brush seals did not fail. Short-duration (46 hr) experimental T-700 engine testing of the compressor discharge seal established over 1-percent engine performance gain (brush versus labyrinth). Long-term gains were established only as leakage comparisons, with the brush at least...
Topics: NASA Technical Reports Server (NTRS), BRUSH SEALS, COMPRESSORS, DURABILITY, ENGINE TESTS, FAILURE...
Flow matching has been successfully achieved for an MHD energy bypass system on a supersonic turbojet engine. The Numerical Propulsion System Simulation (NPSS) environment helped perform a thermodynamic cycle analysis to properly match the flows from an inlet employing a MHD energy bypass system (consisting of an MHD generator and MHD accelerator) on a supersonic turbojet engine. Working with various operating conditions (such as the applied magnetic field, MHD generator length and flow...
Topics: NASA Technical Reports Server (NTRS), PROPULSION SYSTEM PERFORMANCE, TURBOJET ENGINES, ENERGY...
An adaptation of a primitive variable, finite-difference computer program was made in order to predict the non-reacting flow fields in turbojet test cells. The study compares the predictions of the primitive variable computer model with an earlier stream function-vorticity computer model and empirical data. It was found that the model reasonably predicted the flow fields and allowed simulation of test cell flows up to full engine throttle conditions. (Author)
Topics: DTIC Archive, Stevenson,Charles A, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *FLOW FIELDS, *FUEL...
A flight experiment was conducted to investigate air-to-ground propagation of sound near grazing incidence. A turbojet-powered aircraft was flown at low altitudes over the ends of two microphone arrays. An eight-microphone array was positioned along a 1850 m concrete runway. The second array consisted of 12 microphones positioned parallel to the runway over grass. Twenty-eight flights were flown at altitudes ranging from 10 m to 160 m. The acoustic data recorded in the field reduced to...
Topics: NASA Technical Reports Server (NTRS), ACOUSTIC MEASUREMENT, AIRCRAFT NOISE, GRAZING INCIDENCE,...
A comparison was made of the heat transfer characteristics of three air cooled vanes. The vanes incorporated cooling schemes such as impingement cooling, film cooling, and convection cooling with and without extended surfaces. A redesign study was made for two vanes to improve the cooling effectiveness. An average impingement heat transfer coefficient was calculated on the bases of experimentally determined temperatures at the leading edge and a one dimensional heat transfer calculation. This...
Topics: NASA Technical Reports Server (NTRS), AIR COOLING, HEAT TRANSFER, TURBINE BLADES, TURBOJET ENGINES,...
This report covers an evaluation, conducted by the Service Test Division, of the J57-P-8A engine using JP-5 fuel. Two F4D-1 airplanes were utilized for the tests during which one airplane was flown a total of 123.5 hours and the other flown a total of 59.2 hours.
Topics: DTIC Archive, NAVAL AIR TEST CENTER PATUXENT RIVER MD, *JET FIGHTERS, *JET PROPULSION, *TURBOJET...
This document presents the results of a prametric engine cycle study which evaluates the effect of engine cycle on noise and performance of the Production SST. The engine cycles considered are duct burning turbofans, dry turbojets, and afterburning turbojets.
Topics: DTIC Archive, Moruss, A, BOEING COMMERCIAL AIRPLANE CO SEATTLE WA, *TURBOFAN ENGINES, *JET...
378
378
Jun 17, 2010
06/10
by
Hlavin, V. F.; Jonash, E. R.; Smith, A. L
texts
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Combustion performance characteristics of gaseous hydrogen fuel in single tubular turbojet combustor
Topics: COMBUSTION, COMBUSTION CHAMBERS, FUEL COMBUSTION, HYDROGEN, HYDROGEN FUELS, LOW PRESSURE, TURBOJET...
High temperature deposit and oil degradation characteristics of a series of turbojet lubricants were statistically analyzed. Intra-laboratory tests with three oils gave relatively large standard deviation values, but at the 95% probability level showed the oils to be significantly different in demerit value. Inter-laboratory (3 facility) tests of two of these oils showed that the demerit ratings obtained fell statistically within the single laboratory range. Correlation between demerit and...
Topics: DTIC Archive, Harris, J C, MONSANTO RESEARCH CORP DAYTON OH DAYTON LAB, *AIRCRAFT ENGINE OILS,...
The dispersion of the exhaust of turbojet engines into the atmosphere is estimated by using a model developed for the mixing of a round jet with a parallel flow. The analysis is appropriate for determining the spread and dilution of the jet exhaust from the engine exit until it is entrained in the aircraft trailing vortices. Chemical reactions are not expected to be important and are not included in the flow model. Calculations of the dispersion of the exhaust plumes of three aircraft turbojet...
Topics: NASA Technical Reports Server (NTRS), ATMOSPHERIC DIFFUSION, JET EXHAUST, TURBOJET ENGINES, AIR...
This study presents results of a theoretical evaluation of the performance of an afterburning turbofan engine when used for high altitude, high speed flight. The calculated performance is compared with that of a conventional turbojet, and also a combination ramturbojet, by means of the performance parameters of specific fuel consumption and specific thrust. As the study involved a considerable amount of calculations, the problem was coded in Fortran computer language by the writer. The results...
Topics: DTIC Archive, Bell, James F, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *TURBOFAN ENGINES,...
This report presents the results of a study of the acoustic and fluid dynamic characteristics of a shrouded slot nozzle. Experiments were carried out on a slot nozzle of aspect ratio 27 with an ejector shroud having a cross sectional area of four times the primary nozzle area. Parameters varied during the tests were, shroud length, shroud divergence ratio, and acoustical impedance of the shroud wall. Tests were conducted for primary flow Mach numbers from 0.5 to choking and stagnation...
Topics: DTIC Archive, Goethert,B H, TENNESSEE UNIV SPACE INST TULLAHOMA, *TURBOFAN ENGINES, *NOISE...
The effects of contaminated fuel on the performance of turbojet main burner fuel nozzles and the resulting effect on turbojet performance was studied. The fuel used was contaminated with MIL-E-5007B contaminant, plus fungus. The program included a study of the effects of contaminant accumulation on nozzle performance; a study of the effects of poor nozzle performance resulting from the use of contaminated fuel on turbojet performance; nozzle spray tests in which several different nozzles were...
Topics: DTIC Archive, MITCHELL, JAMES P, PRATT AND WHITNEY AIRCRAFT GROUP EAST HARTFORD CT, *FUEL NOZZLES,...
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3.1K
Nov 24, 2012
11/12
by
Mersky, Peter B., 1945-; United States. Marine Corps. History and Museums Division
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A History Of Marine Fighter Attack Squadron 321. "This historical monograph is one of a series of active duty and Reserve squadron histories. When completed, the series will cover each squadron in the Fleet Marine Force. This volume highlights the significant activities of Marine Fighter Attack Squadron 321 during its more than 40 years of active and Reserve service. Since its commissioning in February 1943, the squadron has evolved from a group of inexperienced wartime pilots flying F4U...
Topics: Marine Corps Squadron Histories Series, Fighter planes -- Turbojet engines, Fighter planes --...
Aerodynamic considerations in the design of high performance combustors for turbojet engines are discussed. Aerodynamic problems concerning the preparation of the fuel-air mixture, the recirculation zone where primary combustion occurs, the secondary combustion zone, and the dilution zone were examined. An aerodynamic analysis of the entire primary chamber ensemble was carried out to determine the pressure drop between entry and exit. The aerodynamics of afterburn chambers are discussed. A...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, COMBUSTION CHAMBERS, ENGINE...
Topics: DTIC Archive, WILCOX, FRED, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, *TURBOJET...
The final three months under Contract NO(w)61-0590-d have been spent continuing the study of effects of sulfur in jet fuels and ingested sea water on the durability of engine hot section components.
Topics: DTIC Archive, Streets, W L, PHILLIPS PETROLEUM CO BARTLESVILLE OK, *JET ENGINE FUELS, *SEA WATER,...
NASA Dryden Flight Research Center has completed a preliminary performance analysis of the SR-71 aircraft for use as a launch platform for high-speed research vehicles and for carrying captive experimental packages to high altitude and Mach number conditions. Externally mounted research platforms can significantly increase drag, limiting test time and, in extreme cases, prohibiting penetration through the high-drag, transonic flight regime. To provide supplemental SR-71 acceleration, methods...
Topics: NASA Technical Reports Server (NTRS), PERFORMANCE PREDICTION, SR-71 AIRCRAFT, TURBOJET ENGINES,...
Topics: DTIC Archive, Francois,J, ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND),...
The supersonic cruise aircraft research program identified significant improvements in the technology areas of propulsion, aerodynamics, structures, takeoff and landing procedures, and advanced configuration concepts. Application of these technology areas to a commercial aircraft is discussed. An advanced SST family of aircraft which may be environmentally acceptable, have flexible range-payload capability, and be economically viable is projected.
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, SUPERSONIC COMMERCIAL AIR TRANSPORT,...
The performance of a single-can JT8D combustor was evaluated with Jet A and a high-aromatic diesel fuel over a parametric range of combustor-inlet conditions. Performance parameters investigated were combustion efficiency, emissions of CO, unburned hydrocarbons, and NOx, as well as liner temperatures and smoke. At all conditions the use of diesel fuel instead of Jet A resulted in increases in smoke numbers and liner temperatures; gaseous emissions, on the other hand, did not differ...
Topics: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, DIESEL FUELS, JET ENGINE FUELS,...
A method is developed to interpret flat plate impingement pressure and temperature data taken in jet engine combustor burn-through flames in terms of free stream velocities, pressures, temperatures, etc. These flames, which are high-temperature, turbulent, underexpanded sonic jets, are caused, in practice, by the combustion gases impinging on (and burning a hole through) the wall of the combustor. The free stream property data are needed to compute local heat transfer coefficients, which must...
Topics: DTIC Archive, Pergament, H S, AEROCHEM RESEARCH LABS INC PRINCETON NJ, *COMBUSTION CHAMBERS,...
This report describes a non-intrusive optical technique for determination of liquid mass flux in a droplet laden airstream. The technique was developed for quantitative determination of engine water ingestion resulting from heavy rain or wheel spray. Independent measurements of the liquid water content (LWC) of the droplet laden airstream and of the droplet velocities were made at the simulated nacelle inlet plane for the liquid mass flux determination. The liquid water content was measured by...
Topics: DTIC Archive, Parikh,P, JET PROPULSION LAB PASADENA CA, *INGESTION(ENGINES), *TURBOJET ENGINES,...
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throat area on the performance level of a turbojet engine turbine. The stator blades were bent to increase the throat area in order to move the compressor operating point in the engine farther away from surge. Results are compared with those obtained with the as-cast stator setting.
Topics: NASA Technical Reports Server (NTRS), AIR FLOW, AXIAL FLOW TURBINES, COLD FLOW TESTS, PROPULSION...
A statorless, turbotip lift fan was tested statically outdoors to determine its acoustic characteristics. Spectral and directivity results are presented with comparison to data from the same family of lift fan designs having stator vanes. Modifications to the fan were tested to evaluate circular inlet guide vanes and exhaust treatment. A comparison was made of results obtained at General Electric Edwards Flight Test Center and NASA Ames Research Center with regards to test data and differences...
Topics: NASA Technical Reports Server (NTRS), ACOUSTIC PROPERTIES, LIFT FANS, STATORS, EXHAUST GASES, NOISE...
The in-flight flameout of gas turbine engines, in many instances, is the result of transient reductions in engine air flow caused by many possible conditions such as particular aircraft maneuvers, contamination of intake airflow by exhaust products of self-propelled ordnance launched from aircraft, and severe ice ingestion by the engine. If the aircraft loses altitude or flight speed due to the engine flameout, or must be piloted to lower altitude in order to relight the engine, the mission of...
Topics: DTIC Archive, Rose, John J, WRIGHT AIR DEVELOPMENT CENTER WRIGHT FIELD OH, *FLAMEOUT, *GAS...
