Air Brake Compressor Design for Extended Life and High Performance

1973 ◽  
Author(s):  
Dario R. Gross ◽  
Richard J. Day
Keyword(s):  
High Performance ◽  
Compressor Design ◽  
Extended Life

Design of a High-Performance Axial Compressor for Utility Gas Turbine

1992 ◽  
Vol 114 (2) ◽  
pp. 277-286 ◽  
Author(s):  
A. Sehra ◽  
J. Bettner ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
High Efficiency ◽  
Guide Vane ◽  
Design Flow ◽  
Design Parameters ◽  
Design System ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Compressor Design

An aerodynamic design study to configure a high-efficiency industrial-size gas turbine compressor is presented. This study was conducted using an advanced aircraft engine compressor design system. Starting with an initial configuration based on conventional design practice, compressor design parameters were progressively optimized. To improve the efficiency potential of this design further, several advanced design concepts (such as stator ends bends and velocity controlled airfoils) were introduced. The projected poly tropic efficiency of the final advanced concept compressor design having 19 axial stages was estimated at 92.8 percent, which is 2 to 3 percent higher than the current high-efficiency aircraft turbine engine compressors. The influence of variable geometry on the flow and efficiency (at design speed) was also investigated. Operation at 77 percent design flow with inlet guide vanes and front five variable stators is predicted to increase the compressor efficiency by 6 points as compared to conventional designs having only the inlet guide vane as variable geometry.

scholarly journals Damage-mitigating control of space propulsion systems for high performance and extended life

1993 ◽  
Author(s):  
ASOK RAY ◽  
MIN-KUANG WU ◽  
XIAOWEN DAI ◽  
MARC CARPINO ◽  
CARL LORENZO
Keyword(s):  
High Performance ◽  
Space Propulsion ◽  
Propulsion Systems ◽  
Extended Life

Supersonic Compression Stage Design and Test Results

2004 ◽  
Author(s):  
Shawn P. Lawlor ◽  
John B. Hinkey ◽  
Steven G. Mackin ◽  
Scott Henderson ◽  
Jonathan Bucher ◽  
...  
Keyword(s):  
Power Systems ◽  
High Performance ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Test Results ◽  
Stage Design ◽  
Concept System ◽  
Operational Characteristics ◽  
Compressor Design ◽  
Machinery Design

Ramgen Power Systems, Inc. (RPS) is developing a family of high performance supersonic compressors that combine many of the aspects of shock compression systems commonly used in supersonic flight inlet design with turbo-machinery design practices employed in conventional axial and centrifugal compressor design. The result is a high efficiency compressor that is capable of single stage pressure ratios in excess of those available in existing axial or centrifugal compressors. A variety of design configurations for land-based compressors utilizing this system have been explored. A proof-of-concept system has been designed to demonstrate the basic operational characteristics of this family of compressors when operating on air. The test unit was designed to process ~1.43 kg/s and produce a pressure ratio across the supersonic rotor of 2.25:1. The theory of operation of this system will be reviewed along with selected results from initial performance tests.

Design of a High Performance Axial Compressor for Utility Gas Turbine

1991 ◽  
Author(s):  
A. Sehra ◽  
J. Bettner ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
High Efficiency ◽  
Guide Vane ◽  
Design Flow ◽  
Design Parameters ◽  
Design System ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Compressor Design

An aerodynamic design study to configure a high efficiency industrial-size gas turbine compressor is presented. This study was conducted using an advanced aircraft engine compressor design system. Starting with an initial configuration based on conventional design practice, compressor design parameters were progressively optimized. To further improve the efficiency potential of this design, several advanced design concepts (such as stator ends bends and velocity controlled airfoils) were introduced. The projected polytropic efficiency of the final advanced concept compressor design having 19 axial stages was estimated at 92.8 percent, which is 2 to 3 percent higher than the current high efficiency aircraft turbine engine compressors. The influence of variable geometry on the flow and efficiency (at design speed) was also investigated. Operation at 77 percent design flow with inlet guide vanes and front five variable stators is predicted to increase the compressor efficiency by 6 points as compared to conventional designs having only the inlet guide vane as variable geometry.

Damage-Mitigating Control of Aerospace Systems for High Performance and Extended Life

1992 ◽  
Author(s):  
Asok Ray ◽  
Min-Kuang Wu ◽  
Marc Carpino ◽  
Carl F. Lorenzo ◽  
Walter C. Merrill
Keyword(s):  
High Performance ◽  
Aerospace Systems ◽  
Extended Life

Experimental and Numerical Verification of an Optimization of a Fast Rotating High-Performance Radial Compressor Impeller

2017 ◽  
Vol 139 (10) ◽  
Author(s):  
M. Elfert ◽  
A. Weber ◽  
D. Wittrock ◽  
A. Peters ◽  
C. Voss ◽  
...  
Keyword(s):  
High Performance ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Navier Stokes ◽  
Numerical Verification ◽  
Complex Flow ◽  
Radial Compressor ◽  
Wall Functions ◽  
Numerical Predictions ◽  
Compressor Design

An optimization has been performed on a well-proven radial compressor design known as the SRV4 impeller (the Krain impeller), which has been extensively tested in the past, using the autoopti tool developed at DLR's Institute of Propulsion Technology. This tool has shown its capability in several tasks, mainly for axial compressor and fan design as well as for turbine design. The optimization package autoopti was applied to the redesign and optimization of a radial compressor stage with a vaneless diffusor. This optimization was performed for the SRV4 compressor geometry without fillets using a relatively coarse structured mesh in combination with wall functions. The impeller geometry deduced by the optimization had to be slightly modified due to manufacturing constraints. In order to filter out the improvements of the new so-called SRV5 radial compressor design, two work packages were conducted: The first one was the manufacturing of the new impeller and its installation on a test rig to investigate the complex flow inside the machine. The aim was, first of all, the evaluation of a classical performance map and the efficiency chart achieved by the new compressor design. The efficiencies realized in the performance chart were enhanced by nearly 1.5%. A 5% higher maximum mass flow rate was measured in agreement with the Reynolds-averaged Navier–Stokes (RANS) simulations during the design process. The second work package comprises the computational fluid dynamics (CFD) analysis. The numerical investigations were conducted with the exact geometries of both the baseline SRV4 as well as the optimized SRV5 impeller including the exact fillet geometries. To enhance the prediction accuracy of pressure ratio and impeller efficiency, the geometries were discretized by high-resolution meshes of approximately 5 × 106 cells. For the blade walls as well as for the hub region, the mesh resolution allows a low-Reynolds approach in order to get high-quality results. The comparison of the numerical predictions and the experimental results shows a very good agreement and confirms the improvement of the compressor performance using the optimization tool autoopti.

Conceptual Design of a Supersonic CO2 Compressor

2005 ◽  
Author(s):  
Shawn P. Lawlor ◽  
Peter Baldwin
Keyword(s):  
Power Systems ◽  
Conceptual Design ◽  
High Performance ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Concept System ◽  
New Family ◽  
Operational Characteristics ◽  
Compressor Design ◽  
Machinery Design

Ramgen Power Systems, Inc. (RPS) is developing a family of high performance supersonic compressors that combine many of the aspects of shock compression systems commonly used in supersonic flight inlets with turbo-machinery design practices employed in conventional axial and centrifugal compressor design. The result is a high efficiency compressor that is capable of single stage pressure ratios in excess of those available in existing axial or centrifugal compressors. A variety of design configurations for land-based compressors utilizing this system have been explored. A proof-of-concept system has been designed to demonstrate the basic operational characteristics of this family of compressors when operating on air. The test unit was designed to process ∼1.43 kg/s and produce a pressure ratio across the supersonic rotor of 2.41:1. Based on the results from that effort a compressor specifically designed for the high pressure ratios required to support CO2 liquification has been proposed. The basic theory of operation of this new family of compressors will be reviewed along with the performance characteristics and conceptual design features of the proposed CO2 compressor systems.

Experimental and Numerical Verification of an Optimization of a Fast Rotating High Performance Radial Compressor Impeller

2016 ◽  
Author(s):  
M. Elfert ◽  
A. Weber ◽  
D. Wittrock ◽  
A. Peters ◽  
C. Voss ◽  
...  
Keyword(s):  
High Performance ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Numerical Verification ◽  
Complex Flow ◽  
Radial Compressor ◽  
Wall Functions ◽  
Numerical Predictions ◽  
Compressor Design ◽  
Compressor Impeller

Outgoing from a well-proven radial compressor design which has been extensively being tested in the past known as SRV4 impeller (Krain impeller), an optimization has been performed using the AutoOpti tool developed at DLR’s Institute of Propulsion Technology. This tool has shown its capability in several tasks, mainly for axial compressor and fan design as well as for turbine design. The optimization package AutoOpti was applied to the redesign and optimization of a radial compressor stage with a vaneless diffusor. The numerical results of this optimization were presented by Voss et al. [1] and by Raitor et al. [2]. The optimization was performed for the SRV4 compressor geometry without fillets using a relatively coarse structured mesh in combination with wall functions. The impeller geometry deduced by the optimization had to be slightly modified due to manufacturing constraints. In order to filter out the improvements of the new so-called SRV5 radial compressor design, two work packages were conducted: The first one was the manufacturing of the new impeller and its installation on a test rig to investigate the complex flow inside the machine. The aim was, first of all, the evaluation of a classical performance map and the efficiency chart achieved by the new compressor design. The efficiencies realized in the performance chart were enhanced by nearly 1.5 %. A 5 % higher maximum mass flow rate was measured in agreement with the RANS simulations during the design process. The second work package comprises the CFD analysis. The numerical investigations were conducted with the exact geometries of both, the baseline SRV4 as well as the optimized SRV5 impeller including the exact fillet geometries. To enhance the prediction accuracy of pressure ratio and impeller efficiency the geometries were discretized by high resolution meshes of approximately 5 million cells. For the blade walls as well as for the hub region the mesh resolution allows a low-Reynolds approach in order to get high quality results. The comparison of the numerical predictions and the experimental results shows a very good agreement and confirms the improvement of the compressor performance using the optimization tool AutoOpti.

Approach to High-Performance Transonic Compressor Design

2004 ◽  
Vol 20 (1) ◽  
pp. 164-170 ◽  
Author(s):  
M. Oana ◽  
O. Kawamoto ◽  
H. Ohtani ◽  
Y. Yamamoto
Keyword(s):  
High Performance ◽  
Transonic Compressor ◽  
Compressor Design
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