scholarly journals A Turbojet Simulator for Mach Numbers up to 2.0

1972 ◽  
Author(s):  
F. W. Steffen ◽  
E. A. Satmary ◽  
M. R. Vanco ◽  
S. M. Nosek
Keyword(s):  
High Pressure ◽  
Wind Tunnel ◽  
Axial Flow ◽  
Calibration Procedure ◽  
Aerodynamic Design ◽  
Flight Data ◽  
Axial Flow Compressor ◽  
Heated Air ◽  
Turbojet Engine ◽  
Flow Compressor

A turbojet simulator has been designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and temperature. Overall aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.

Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

1961 ◽  
Vol 83 (3) ◽  
pp. 303-320 ◽  
Author(s):  
Karl Kovach ◽  
D. M. Sandercock
Keyword(s):  
Research Work ◽  
Axial Flow ◽  
Performance Characteristics ◽  
Research Center ◽  
Aerodynamic Design ◽  
Axial Flow Compressor ◽  
Turbojet Engine ◽  
And Performance ◽  
Flow Compressor ◽  
Work Done

A five-stage axial-flow compressor with all rotors operating with transonic relative inlet Mach numbers was designed as a research vehicle at the Lewis Research Center in 1952. The compressor was designed and tested as a component of a turbojet engine. This paper summarizes the research work done on this compressor including the aerodynamic design and detailed performance characteristics.

Highly-Loaded Low-Reaction Boundary Layer Suction Axial Flow Compressor

2007 ◽  
Author(s):  
Songtao Wang ◽  
Xiaoqing Qiang ◽  
Weichun Lin ◽  
Guotai Feng ◽  
Zhongqi Wang
Keyword(s):  
Boundary Layer ◽  
High Pressure ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Design Concept ◽  
Axial Flow Compressor ◽  
Boundary Layer Suction ◽  
High Pressure Ratio ◽  
Flow Compressor ◽  
Highly Loaded

In order to design high pressure ratio and highly loaded axial flow compressor, a new design concept based on Highly-Loaded Low-Reaction and boundary layer suction was proposed in this paper. Then the concept’s characteristics were pointed out by comparing with the MIT’s boundary layer suction compressor. Also the application area of this design concept and its key technic were given out in this paper. Two applications were carried out in order to demonstrate the concept. The first application was to redesign a low speed duplication-stage axial flow compressor into a single stage. The second one was a feasibility analysis to decrease an 11 stage axial compressor’s stage count to 7 while not changing its aerodynamic performance. The analysis result showed that the new design concept is feasible and it can be used on high pressure stage of the aero-engine, compressor of ground gas turbine (except the transonic stage) and high total pressure ratio blower.

Aerodynamic Design and Testing of an Axial Flow Compressor for the GT24/26 Gas Turbines

2013 ◽  
Author(s):  
Damir Novak ◽  
Michael Loetzerich ◽  
Matthias Boese
Keyword(s):  
Gas Turbines ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Leading Edge ◽  
Advanced Technology ◽  
Aerodynamic Design ◽  
3D Design ◽  
Axial Flow Compressor ◽  
Stage Matching ◽  
Flow Compressor

A 22-stage axial flow compressor with a pressure ratio 35:1 has been designed, built and successfully tested for a heavy-duty gas turbine application. Advanced technology and aero engine design tools have been used. The compressor has been designed using an “arbitrary” airfoil blading including 3D design features, like leading edge re-camber, lean, sweep and flowpath contouring. The compressor performance and part load behavior have been improved by accurate stage matching based on whole compressor 3D analyses. The new compressor has been tested in a scaled down rig and validated in the Alstom Test Power Plant (ATPP).The compressor met all design objectives and demonstrated excellent performance. This paper describes the aerodynamic design and test results.

Axial flow compressor design†

1999 ◽  
Vol 213 (5) ◽  
pp. 437-449 ◽  
Author(s):  
S. J. Gallimore
Keyword(s):  
Design Process ◽  
Axial Flow ◽  
Point Of View ◽  
Aerodynamic Design ◽  
Basic Principles ◽  
Axial Flow Compressor ◽  
Compressor Design ◽  
Aero Engines ◽  
Flow Compressor ◽  
Practical Constraints

The purpose of this paper is to set out some of the basic principles and rules associated with the design of axial flow compressors, principally for aero-engines, as well as the practical constraints that are inevitably present. The thrust is primarily on the aerodynamic design but this cannot be divorced from the mechanical aspects and so some of these are touched upon but are not gone into so deeply. The paper has been written from the point of view of the designer and tries to cover most of the points that need to be considered in order to produce a successful compressor. The emphasis has been on the theory behind the design process and on minimizing the reliance on empirical rules. However, because of the complexity of the flow, some empiricism still remains.

The J83 Seven-Stage Transonic Compressor

1961 ◽  
Vol 83 (3) ◽  
pp. 291-301 ◽  
Author(s):  
J. A. King
Keyword(s):  
High Performance ◽  
Axial Flow ◽  
Axial Flow Compressor ◽  
Transonic Compressor ◽  
Turbojet Engine ◽  
Flow Compressor ◽  
Maximum Thrust

The J83 turbojet engine was a high-performance, lightweight engine with a maximum thrust of 2450 lb, a diameter of 18 in., and a weight of approximately 300 lb. The compressor for this engine was a seven-stage, transonic, axial-flow compressor with an inlet tip diameter of 15.2 in. and a hub-lip ratio of 0.433. Details of the aero-thermodynamic design of this compressor and the problems encountered during its development are given in this paper.

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