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Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey
Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure are provided.
Date:
May 23, 1955
Creator:
Calvert, Howard F.; Medeiros, Arthur A. & Garrett, Floyd B.
System:
The UNT Digital Library
Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 5: preliminary analysis of over-all performance of modified compressor
Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are provided.
Date:
May 23, 1955
Creator:
Standahar, Raymond M. & Geye, Richard P.
System:
The UNT Digital Library
Preliminary Results of the Determination of Inlet-Pressure Distortion Effects on Compressor Stall and Altitude Operating Limits of the J57-P-1 Turbojet Engine
"During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the high- and low-speed engine operating limits were investigated up to the maximum operable altitude" (p. 1).
Date:
May 23, 1955
Creator:
Wallner, L. E.; Lubick, R. J. & Chelko, L. J.
System:
The UNT Digital Library
Turboprop-engine design considerations 1: effect of mode of engine operation on performance of turboprop engine with current compressor pressure ratio
Report presenting a cycle analysis of a turboprop engine for various modes of operation over a range of flight conditions in order to determine whether one mode of operation has any marked advantages. The methods of operation explored included constant compressor equivalent design speed, constant design engine rotative speed, adjustable turbine stators, and variable exhaust-nozzle area.
Date:
May 23, 1955
Creator:
Davison, Elmer H.
System:
The UNT Digital Library
Turboprop-engine design considerations 2: design requirements and performance of turboprop engines with a single-spool high-pressure-ratio compressor
Report of an investigation of the effect of mode of engine operation, engine configuration, and airplane flight condition on the performance and design requirements of a turboprop engine with a high-pressure-ratio single-spool compressor. Both single-spool engines and gas-generating engines are considered. The free-turbine engine was found to be less versatile than the single-spool engine because the range of turbine-inlet temperature over which it can operate is restricted.
Date:
May 23, 1955
Creator:
Davison, Elmer H. & Stalla, Margaret C.
System:
The UNT Digital Library