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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 91 records · Page 5

All sources NASA NTRS DOE OSTI

NASA NTRS1949

Performance of J33 turbojet engine with shaft-power extraction III : turbine performance

The performance of the turbine component of a J33 turbojet engine was determined over a range of turbine speeds from 8000 to 11,500 rpm.Turbine-inlet temperature was varied from the minimum required to drive the compressor to a maximum of approximately 2000 degrees R at each of several intermediate turbine speeds. Data are presented that show the horsepower developed by the turbine per pound of gas flow. The relation between turbine-inlet stagnation pressure, turbine-outlet stagnation pressure, and turbine-outlet static pressure was established. The turbine-weight-flow parameter varied from 39.2 to 43.6. The maximum turbine efficiency measured was 0.86 at a pressure ratio of 3.5 and a ratio of blade speed to theoretical nozzle velocity of 0.39. A generalized performance map of the turbine-horsepower parameter plotted against the turbine-speed parameter indicated that the best turbine efficiency is obtained when the turbine power is 10 percent greater than the compressor horsepower. The variation of efficiency with the ratio of blade speed to nozzle velocity indicated that the turbine operates at a speed above that for maximum efficiency when the engine is operated normally with the 19-inch-diameter jet nozzle.

Huppert, M C↗

NASA NTRS1952

Loiter performance of turbojet-powered aircraft performance determined by off-design cycle analysis

Loitering performance of airplanes equipped with various turbojet engines was analytically investigated. The engines used in this analysis were selected to show the effects of various engine design variables. Engine performance was determined by means of an off-design cycle analysismaking use of experimentally determined component characteristics. The method of off-design cycle analysis is presented herein and is verified by a check with experimental data.

Koutz, Stanley L↗

NASA NTRS1998

Integrated Advanced Microwave Sounding Unit-A(AMSU-A). Performance Verification Reports: Final Comprehensive Performance Test Report, P/N: 1356008-1-TST, S/N: 202/A1

This is the Performance Verification Report, Final Comprehensive Performance Test Report, P/N 1356008-1-TST, S/N 202/A1 for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Haigh, R.↗

NASA NTRS1998

Intergrated Advanced Microwave Sounding Unit-A (AMSU-A) Performance Verification Reports: Initial Comprehensive Performance Test Report, P/N: 1356006-1-IT, S/N: 202/A2

This Performance Verification Report is for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A), Initial Comprehensive Performance Test Report, P/N 1356006- 1 -IT, S/N: 202/A2.

Platt, R.↗

NASA NTRS1998

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Reports: Initial Comprehensive Performance Test Report, P/N: 1356008-1-IT, S/N: 202/A1

This is the Performance Verification Report, Initial Comprehensive Performance Test Report, P/N 1356008-1-IT, S/N 202/A1, for the Integrated Advanced Microwave Sounding Unit (AMSU-A).

Haigh, R.↗

NASA NTRS1999

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Final Comprehensive Performance Test Report, P/N 1331200-2, S/N 105/A2

This is the Performance Verification Report, Final Comprehensive Performance Test Report, P/N 1331200-2, S/N 105/A2, for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Platt, R.↗

NASA NTRS1998

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Initial Comprehensive Performance Test Report, P/N 1331720-2, S/N 105

This is the Performance Verification Report, Initial Comprehensive Performance Test Report, P/N 1331720-2, S/N 105, for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Platt, R.↗

NASA NTRS2000

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Initial Comprehensive Performance Test Report, P/N 1331200-2-IT, S/N 108/A2

This is the Performance Verification Report, Initial Comprehensive Performance Test Report, P/N 1331200-2-IT, S/N 108/A2, for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Linn, J.↗

NASA NTRS2000

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Final Comprehensive Performance Test Report, P/N 1331200-2-TST, S/N 108/A2

This is the Performance Verification Report, Final Comprehensive Performance Test Report, P/N 1331200-2-TST, S/N 108/A2, for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Linn, J.↗

NASA NTRS2000

Integrated Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Initial Comprehensive Performance Test Report, PN 1331720-3-IT, S/N 109/A1

This is the Performance Verification Report, Initial Comprehensive Performance Test Report, P/N 1331720-2-IT, S/N 108/Al, for the Integrated Advanced Microwave Sounding Unit-A (AMSU-A).

Source record↗

NASA NTRS2000

Integrated-Advanced Microwave Sounding Unit-A (AMSU-A). Performance Verification Report: Final Comprehensive Performance Test Report, P/N 1331720-3-TST, S/N 109/A1

This is the performance Verification Report, Final Comprehensive Performance Test Report, P?N 1331720-3-TST, S/N 109/A1, for the Integrated-Advanced Microwave Sounding Unit-A (AMSU-A).

Source record↗

NASA NTRS1997

High Performance Input/Output Systems for High Performance Computing and Four-Dimensional Data Assimilation

The approach of this task was to apply leading parallel computing research to a number of existing techniques for assimilation, and extract parameters indicating where and how input/output limits computational performance. The following was used for detailed knowledge of the application problems: 1. Developing a parallel input/output system specifically for this application 2. Extracting the important input/output characteristics of data assimilation problems; and 3. Building these characteristics s parameters into our runtime library (Fortran D/High Performance Fortran) for parallel input/output support.

Fox, Geoffrey C.↗

NASA NTRS1952

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor. II - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 deg

The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.

Hatch, James E.↗

NASA NTRS1952

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor. III - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages

The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.

Medeiros, Arthur A.↗

NASA NTRS1952

Effect of Various Blade Modifications on Performance of a 16-Stage High-pressure-ratio Axial-flow Compressor.Angles 3 deg: Effect on Over-all Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-blade Angles 3 deg - 1

The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.

Medeiros, Arthur A.↗

NASA NTRS2010

Alternate-Fueled Combustor-Sector Performance: Part A: Combustor Performance Part B: Combustor Emissions

Alternate aviation fuels for military or commercial use are required to satisfy MIL-DTL-83133F(2008) or ASTM D 7566 (2010) standards, respectively, and are classified as drop-in fuel replacements. To satisfy legacy issues, blends to 50% alternate fuel with petroleum fuels are certified individually on the basis of feedstock. Adherence to alternate fuels and fuel blends requires smart fueling systems or advanced fuel-flexible systems, including combustors and engines without significant sacrifice in performance or emissions requirements. This paper provides preliminary performance (Part A) and emissions and particulates (Part B) combustor sector data for synthetic-parafinic-kerosene- (SPK-) type fuel and blends with JP-8+100 relative to JP-8+100 as baseline fueling.

Shouse, D. T.↗

NASA NTRS2010

Facilitating NASA's Use of GEIA-STD-0005-1, Performance Standard for Aerospace and High Performance Electronic Systems Containing Lead-Free Solder

GEIA-STD-0005-1 defines the objectives of, and requirements for, documenting processes that assure customers and regulatory agencies that AHP electronic systems containing lead-free solder, piece parts, and boards will satisfy the applicable requirements for performance, reliability, airworthiness, safety, and certify-ability throughout the specified life of performance. It communicates requirements for a Lead-Free Control Plan (LFCP) to assist suppliers in the development of their own Plans. The Plan documents the Plan Owner's (supplier's) processes, that assure their customer, and all other stakeholders that the Plan owner's products will continue to meet their requirements. The presentation reviews quality assurance requirements traceability and LFCP template instructions.

Plante, Jeannete↗

NASA NTRS2012

Predicting the Impacts of Intravehicular Displays on Driving Performance with Human Performance Modeling

A challenge facing the U.S. National Highway Traffic Safety Administration (NHTSA), as well as international safety experts, is the need to educate car drivers about the dangers associated with performing distraction tasks while driving. Researchers working for the U.S. Army Research Laboratory have developed a technique for predicting the increase in mental workload that results when distraction tasks are combined with driving. They implement this technique using human performance modeling. They have predicted workload associated with driving combined with cell phone use. In addition, they have predicted the workload associated with driving military vehicles combined with threat detection. Their technique can be used by safety personnel internationally to demonstrate the dangers of combining distracter tasks with driving and to mitigate the safety risks.

Mitchell, Diane Kuhl↗