The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading: Part I — University Research and Methods Development

2002 ◽  
Author(s):  
Simon J. Gallimore ◽  
John J. Bolger ◽  
Nicholas A. Cumpsty ◽  
Mark J. Taylor ◽  
Peter I. Wright ◽  
...  
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Essential Element ◽  
University Research ◽  
Low Speed ◽  
High Speed Engine ◽  
Methods Development ◽  
Basic Ideas ◽  
Flow Compressor ◽  
The University

This paper describes the introduction of 3D blade designs into the core compressors for the Rolls-Royce Trent engine with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to the application to high pressure engine compressors. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. The first part of the paper concentrates on the university-based research and the methods development. The second part describes additional low-speed multistage design and testing and the high-speed engine compressor design and test.

The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part I: University Research and Methods Development

2002 ◽  
Vol 124 (4) ◽  
pp. 521-532 ◽  
Author(s):  
Simon J. Gallimore ◽  
John J. Bolger ◽  
Nicholas A. Cumpsty ◽  
Mark J. Taylor ◽  
Peter I. Wright ◽  
...  
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Essential Element ◽  
University Research ◽  
Low Speed ◽  
High Speed Engine ◽  
Methods Development ◽  
Basic Ideas ◽  
Flow Compressor ◽  
The University

This paper describes the introduction of 3-D blade designs into the core compressors for the Rolls-Royce Trent engine with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to the application to high pressure engine compressors. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. The first part of the paper concentrates on the university-based research and the methods development. The second part describes additional low-speed multistage design and testing and the high-speed engine compressor design and test.

The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading: Part II — Low and High Speed Designs and Test Verification

2002 ◽  
Author(s):  
Simon J. Gallimore ◽  
John J. Bolger ◽  
Nicholas A. Cumpsty ◽  
Mark J. Taylor ◽  
Peter I. Wright ◽  
...  
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Essential Element ◽  
Low Speed ◽  
High Speed Engine ◽  
Methods Development ◽  
Engine Compressor ◽  
Basic Ideas ◽  
Flow Compressor ◽  
Test Verification

This paper describes the introduction of 3D blade designs into the core compressors of the Rolls-Royce Trent engine series with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to their application to the high pressure engine compressor. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. Part I of the paper concentrated on the fundamental university-based research and the methods development. Part II describes additional low-speed multistage design and testing and the high-speed engine compressor designs and tests.

The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading—Part II: Low and High-Speed Designs and Test Verification

2002 ◽  
Vol 124 (4) ◽  
pp. 533-541 ◽  
Author(s):  
Simon J. Gallimore ◽  
John J. Bolger ◽  
Nicholas A. Cumpsty ◽  
Mark J. Taylor ◽  
Peter I. Wright ◽  
...  
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Essential Element ◽  
Low Speed ◽  
High Speed Engine ◽  
Methods Development ◽  
Engine Compressor ◽  
Basic Ideas ◽  
Flow Compressor ◽  
Test Verification

This paper describes the introduction of 3-D blade designs into the core compressors of the Rolls-Royce Trent engine series with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to their application to the high pressure engine compressor. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. Part I of the paper concentrated on the fundamental university-based research and the methods development. Part II describes additional low-speed multistage design and testing and the high-speed engine compressor designs and tests.

Optimized Preliminary Design of a Multistage Low-Speed Axial FLow Compressor

2021 ◽  
Author(s):  
AbdelRahman Ahmed Kamal ◽  
Alyaa Abdelnaby Thabet ◽  
Mohamed M. A. Elnabawy
Keyword(s):  
Axial Flow ◽  
Preliminary Design ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Flow Compressor

The Manufacture of Glass Cloth/Resin Blades for an Axial Flow Compressor

1954 ◽  
Vol 58 (522) ◽  
pp. 434-434
Author(s):  
J. H. Horlock
Keyword(s):  
Polyester Resin ◽  
Axial Flow ◽  
Glass Cloth ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Flow Compressor ◽  
The University

Glass Cloth/Polyester resin laminates similar to those described by Irving and Saunders (Journal, February 1954) have been used at the University Engineering Laboratory, Cambridge, in the manufacture of blades for an axial flow compressor. In the first experiments, an existing aluminium stator blade was used as a pattern, and a mould was made by pouring molten type metal round this pattern, held in a steel sided moulding box.

Stall cell blockage in a high-speed multistage axial-flow compressor

1990 ◽  
Author(s):  
STEVEN GORRELL ◽  
WILLIAM COPENHAVER ◽  
WALTER O'BRIEN
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Flow Compressor

Effect of Axially Non-Uniform Rotor Tip Clearance on the Performance of a High Speed Axial Flow Compressor Stage

1994 ◽  
Author(s):  
K. Mohan ◽  
S. A. Guruprasad
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Separated Flow ◽  
Tip Clearance ◽  
Compressor Stage ◽  
Tip Leakage Flow ◽  
Suction Surface ◽  
Wall Boundary Layer ◽  
Improved Performance ◽  
Flow Compressor

An axially non-uniform type of rotor tip clearance was conceived and tried on a single stage compressor. This concept is based on the advantages of a smaller tip clearance in the front portion of the blade and a larger clearance in the rear portion which allows a higher tip leakage flow to interact with the passage secondary flow, casing wall boundary layer, separated flow on the blade suction surface and the scraping vortex, which are more prominent at the rear portion of the blade. Experimental results indicated that an axially non-uniform clearance can provide improved performance of a compressor stage. Providing the tip clearance in the compressor casing instead of at the blade tip indicated certain advantages. An ‘optimum’ value of rotor tip clearance was noticed for this compressor stage, both for axially uniform and axially non-uniform clearance.

scholarly journals The Numerical Simulation of a High-Speed Axial Flow Compressor

1991 ◽  
Author(s):  
Richard A. Mulac ◽  
John J. Adamczyk
Keyword(s):  
Numerical Simulation ◽  
Data Storage ◽  
High Speed ◽  
Axial Flow ◽  
Equation System ◽  
Axial Flow Compressor ◽  
Code Performance ◽  
Recent Developments ◽  
Multistage Compressors ◽  
Flow Compressor

The advancement of high-speed axial flow multistage compressors is impeded by a lack of detailed flow field information. Recent developments in compressor flow modeling and numerical simulation have the potential to provide needed information in a timely manner. This paper, which consists of two parts, will explore this topic. The first part will address the development of a computer program to solve the viscous form of the average-passage equation system for multistage turbomachinery. Programming issues such as in-core versus out-of-core data storage and CPU utilization (parallelization, vectorization, and chaining) will be addressed. Code performance will be evaluated through the simulation of the first four stages of a five stage, high-speed, axial flow compressor on a CRAY Y-MP8/8128 computer. The second part will address the flow physics which can be obtained from the numerical simulation. In particular, an examination of the endwall flow structure will be made, and its impact on blockage distribution assessed.

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