Author: Robert W. GrahamPublisher:
ISBN:
Category :
Languages : en
Pages : 34
Book Description
Experimental and Theoretical Investigation of Rotating-stall Characteristics of Single-stage Axial-flow Compressor with Hub-tip Ratio of 0.76
Author: Robert W. GrahamRotating Stall Investigation of the 0.72 Hub-tip Ratio Single-stage Compressor
Author: Robert W. GrahamPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 30
Book Description
Investigation of Rotating Stall in a Single-stage Axial Compressor
Author: S. R. MontgomeryPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 28
Book Description
The rotating-stall characteristics of a single-stage axial-flow compressor were investigated. The number of stall cells and their propagation velocities were found with and without stator blades. The measured velocities were compared with those predicted by Stenning's theory (see NACA TN 3580), assuming the dounstream pressure fluctuations to be negligible, and correlation within 10 percent was obtained at the onset of stall. It was found that the pressure fluctuations cauased by rotating stall were less downstream of the rotor than upstream; the minimum reduction across the rotor was 40 percent with stator blades and 75 percent without stator blades. It was also that, for the compressor tested, the stator blades decreased the number of stall cells and tended to induce rotating stall at larger mass flow rates.
Investigation of Rotating Stall in a Single Stage Axial Compressor
Author: Massachusetts Institute of Technology. Gas Turbine LaboratoryPublisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 31
Book Description
Investigation of Rotating Stall in Axial Flow Compressors and the Development of a Prototype Rotating Stall Control System
Author: Gary R. LudwigPublisher:
ISBN:
Category :
Languages : en
Pages : 283
Book Description
The report summarizes the results of a three year program on rotating stall in axial flow compressors conducted at Calspan Corporation (formerly Cornell Aeronautical Laboratory). The work encompassed both experimental and theoretical investigations of rotating stall and the development of a prototype rotating stall control system. The experimental portion of the program included investigation of the effects of blade chord and solidity upon rotating stall properties and inception as well as an investigation of the effect of blade row rotation on blade row performance. In addition, an experiment to determine the stability of the flow through a blade row was conducted. A two-dimensional small-disturbance stability theory was developed to predict the inception of rotating stall. A single balde row and two blade row version of the theory were developed.
Subject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)Publisher:
ISBN:
Category : Industrial arts
Languages : en
Pages : 906
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.
Investigation of a 1500 Ft/sec, Transonic, High-through-Flow, Single- Stage Axial-Flow Compressor with Low Hub/Tip Ratio
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 375
Book Description
Complete experimental results are presented from tests of an axial compressor stage designed for a flow per frontal area of 39.7 lb/sec/ft square, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. Since the most serious aerodynamic design problems of the over-all compressor were observed to be associated with the first stage, this stage was chosen as the subject of a research program. Results of the tests indicated that, at design speed, design flow was achieved with a rotor isentropic efficiency of 90.4 percent, a stage isentropic efficiency of 88.2 percent and a stage total pressure ratio of 2.065.
Author: Jacques Valensi
Author: