Author: Hans Georg Mokelke
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Circumferential inlet flow distortions in multi-stage axial compressors
Author: Hans Georg Mokelke
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The Attenuation of Circumferential Inlet Distortion in Multi-stage Axial Compressors
Author: G. A. Plourde
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 11
Book Description
Circumferential Inlet Distortions in an Axial Flow Compressor
Author: Frank R. Carter
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 38
Book Description
Analysis of Internal Flow of J85-13 Multistage Compressor
Author: Roy D. Hager
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 22
Book Description
The Development of Inlet Flow Distortions in Multi-stage Axial Compressors of High-tip Ratio
Author: H. Mokelke
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Internal Flow Characteristics of a Multistage Compressor with Inlet Pressure Distortion
Author: Claude E. DeBogdan
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 44
Book Description
Compressor Instability with Integral Methods
Author: Eddie Y.K. Ng
Publisher: 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.
Publisher: 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.
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
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
Inlet Flow Distortions in Axial Flow Compressors
Author: Jean Colpin
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Book Description
Compressibility Effects in Circumferential Inlet Distortion in Axial Compressors
Author: Zbigniew Krzywoblocki
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 42
Book Description
Publisher:
ISBN:
Category : Compressibility
Languages : en
Pages : 42
Book Description