Dynamic Inlet Distortion Experiments on a Two-stage Transonic Compressor PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Dynamic Inlet Distortion Experiments on a Two-stage Transonic Compressor PDF full book. Access full book title Dynamic Inlet Distortion Experiments on a Two-stage Transonic Compressor by R. K. Oldham. Download full books in PDF and EPUB format.
Author: R. K. Oldham
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Get Book Here
Book Description
Author: R. K. Oldham
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Get Book Here
Book Description
Author: Zoltán Sándor Spakovszky
Publisher:
ISBN:
Category :
Languages : en
Pages : 103
Get Book Here
Book Description
Author: Leon M. Wenzel
Publisher:
ISBN:
Category : Compressors
Languages : en
Pages : 26
Get Book Here
Book Description
Author: William H. Robbins
Publisher:
ISBN:
Category :
Languages : en
Pages : 105
Get Book Here
Book Description
Author: Mikkel Andreas Unrau
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
Get Book Here
Book Description
Accurately predicting fan performance, including bounds of operation, is an important function of any Computational Fluid Dynamics (CFD) package. The presented research uses a CFD code developed as part of the Computational Research and Engineering Acquisition Tools and Environment (CREATE), known as Kestrel, to evaluate a single stage compressor at various operating conditions. Steady-state, single-passage simulations are carried out to validate capabilities recently added to Kestrel. The analysis includes generating speedlines of total pressure ratio and efficiency, as well as radial total temperature and total pressure profiles at two axial locations in the compressor at various operating conditions and fan speeds, and simulation data from the single-passage runs is compared to experimental data. Time-accurate, full annulus simulations are also carried out to capture and analyze the processes leading to stall inception for both uniform and distorted inlet conditions. The distortion profile used contains at 90° sector of lower total pressure at the inlet. The observed fan behavior at stall inception is compared to previous research, and it is concluded that the inlet distortion significantly changes the behavior of the part-span stall cells that develop after stall inception. Understanding the physical processes that lead to stall inception allows fan designers to design more robust fans that can safely take advantage of the better performance associated with operating closer to stall.
Author: Wolfram Pazur
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 0
Get Book Here
Book Description
Aeroengine intakes containing S-shaped diffusers produce different types of inlet swirl distortions and essentially a combination of a twin swirl and a bulk swirl. The main object of this investigation was to assess the influence of inlet swirl distortions on the performance of a transonic two-stage axial compressor installed in a turbo jet bypass engine Larzac 04. A typical inlet swirl distortion was simulated by a delta-wing in front of the engine. An experimental method was investigated to measure the performance map of the installed low-pressure compressor for different engine operating lines. The influence of an inlet swirl distortion with different strengths on the performance map of the compressor was investigated experimentally. It is shown that the performance parameters decrease and a temperature distortion is generated behind the compressor. As the basis of the theoretical investigations of the performance map, including inlet swirl distortions, a computing model considering four compressors working in parallel was established. The model is based on the idea that an inlet swirl distortion can be substituted by two fundamental types of swirl components, i.e., a bulk swirl corotating, and a bulk swirl counterrotating to the revolution of the compressor. Computed performance maps of the compressor will be discussed and compared with the experimental data.
Author: D. Rabe
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723255342
Category :
Languages : en
Pages : 26
Get Book Here
Book Description
An investigation of surge was conducted by using a parallel compressor model of the J85-13 compressor implement on an analog computer. Surges were initiated by various types of dynamic disturbances in inlet pressure. The compressor model was less sensitive to disturbances of short duration, high frequency, and long duration where the compressor discharge pressure could react. Adding steady distortion to dynamic disturbances reduced the amount of dynamic disturbance required to effect surge. Steady and unsteady distortions combined linearly to reduce surge margin. Wenzel, L. M. and Blaha, R. J. Glenn Research Center NASA-TM-X-3522, E-8979 RTOP 505-05
Author:
Publisher:
ISBN:
Category : Aerothermodynamics
Languages : en
Pages : 770
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
Get Book Here
Book Description
