Author: Ross Bakke GridleyPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 176
Book Description
Performance Characteristics of an Axial-flow Compressor Operating with Circumferential Inlet Flow Distortion
Author: Ross Bakke GridleyPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 176
Book Description
Performance and Stalling Behavior of an Axial Flow Compressor with Circumferential Inlet Flow Distortion
Author: Billy Brice DancyPublisher:
ISBN:
Category :
Languages : en
Pages : 274
Book Description
Performance and Stalling Behavior of an Axial-flow Compressor Subjected to Three Circumferential Inlet Distortion Levels
Author: William H. GaudenPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 238
Book Description
Compressor Instability with Integral Methods
Author: Eddie Y.K. NgPublisher: Springer Science & Business Media
ISBN: 3540724125
Category : Technology & Engineering
Languages : en
Pages : 154
Book Description
This book brings together the quick integral approaches and advances in the field for the prediction of stall and surge problems in the compressor. The book is useful for people involved in the flow analysis, design and testing of rotating machinery. For students, it can be used as a specialized topic of senior undergraduate or graduate study. The book can also serve as self-study material.
Performance of a J85-13 Compressor with Clean and Distorted Inlet Flow
Author: Edward J. MilnerPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
Book Description
The results presented are of a series of experimental tests in which a J85-13 turbojet engine was subjected to both distorted and undistorted inlet total pressure conditions. A distinctive feature of the data base obtained is that it includes compressor interstage information not previously recorded for a J85-13 engine. Each of the eight compressor stages was instrumented to obtain the characteristics of the individual stages for undistorted inlet conditions, and these data are documented in the report along with the undistorted compressor overall performance. Also included in the report is the overall performance of the compressor exposed to 14 different distorted-inlet conditions - 10 circumferential patterns and 4 radial patterns. The distortion patterns were introduced using screens that spoiled from 8 to 50 percent of the compressor face area; the distortion screen density, or the area blocked by the screen wire per unit area of screen, varied from 26 to 69 percent.
Effect of Circumferential Total-pressure Gradients Typical of Single-inlet Duct Installations on Performance of an Axial-flow Turbojet Engine
Author: S. C. HuntleyPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 38
Book Description
Experimental Investigation of the Effect of Circumferential Inlet Flow Distortion on the Performance of a Five-stage Axial-flow Research Compressor with Transonic Rotors in All Stages
Author: William H. RobbinsPublisher:
ISBN:
Category :
Languages : en
Pages : 105
Book Description
Task IV
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721585243
Category :
Languages : en
Pages : 24
Book Description
The concepts and the procedure developed in Task I and Task III were used to determine the response of an eleven-stage high-speed compressor to an inlet distortion of 180 deg. circumferential extent for contrasting against its performance under uniform inlet flow. Using the computed results at the inlet to and outlet of the compressor, the computed total pressure ratio and efficiency for the clean condition are determined to be 14.22 and 76.9 percent respectively. As for the distorted case, these are determined to be 10.35 and 71.8 percent respectively, showing deterioration 76.9 percent vs 71.8 percent). The physical consistency of the computed flow field was assessed as a means of demonstrating the applicability and utility of the body force representation for inlet distortion computations. Specifically the computed evolution of the distorted pattern in static pressure and total pressure from compressor inlet to exit is examined. For the eleven-stage compressor examined here, the deterioration in performance has been found to be particularly severe in the last 2 stages. This suggests that the last two stages could be redesigned to alleviate the observed deterioration thus making the compressor performance insensitive to circumferential inlet distortion. This can potentially be accomplished by first determining what should the body force distribution of the last two stages should be to achieve minimal or no deterioration in performance in the last two stages. One can then in principle proceed to determine the blade design to yield such a body force distribution. Tan, Choon-Sooi and Suder, Kenneth (Technical Monitor) Glenn Research Center
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.
Analysis of Internal Flow of J85-13 Multistage Compressor
Author: Roy D. HagerPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 22
Book Description
