Author: Seymour M. BogdonoffPublisher:
ISBN:
Category :
Languages : en
Pages : 34
Book Description
The Performance of Axial-Flow Compressors as Affected by Single Stage Characteristics
Author: Seymour M. BogdonoffPublisher:
ISBN:
Category :
Languages : en
Pages : 34
Book Description
ASME 57-A-139
Author: Aubrey StonePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 17
Book Description
Aerodynamic Design of Axial-flow Compressors
Author: Lewis Research CenterPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 542
Book Description
Aerodynamic Design of Axial Flow Compressors
Author: Robert O. BullockPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 552
Book Description
Performance of Single-stage Axial-flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26 Respectively, and with Design Pressure Ratio of 2.05
Author: Royce D. MoorePublisher:
ISBN:
Category :
Languages : en
Pages : 108
Book Description
Design and Tests of a Six-stage Axial-flow Compressor Having a Tip Speed of 550 Feet Per Second and a Flat Operating Characteristic at Constant Speed
Author: Willard R. WestphalPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 66
Book Description
A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.
Matched Performance Characteristics of a 16 Stage Axial-flow Compressor and a 3 Stage Turbine
Author: John J. Jr RebeskePublisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
End Wall Flow Characteristics and Overall Performance of an Axial Flow Compressor Stage
Author: N. SitaramPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 148
Book Description
Performance of Single-stage Axial-flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and with Design Pressure Ration of 1.82
Author: Lonnie ReidPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 110
Book Description
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 854
Book Description
