Design of a Rotor Incorporating Splitter Vanes for a High Pressure Ratio Supersonic Axial Compressor Stage

1974 ◽  
Author(s):  
Arthur J. Wennerstrom ◽  
George R. Frost
Keyword(s):  
High Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Compressor Stage ◽  
High Pressure Ratio

Aerodynamic Design and Analysis of a High Pressure Ratio Aspirated Compressor Stage

2000 ◽  
Author(s):  
Ali A. Merchant ◽  
Mark Drela ◽  
Jack L. Kerrebrock ◽  
John J. Adamczyk ◽  
Mark Celestina
Keyword(s):  
Boundary Layer ◽  
Total Pressure ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Adverse Pressure Gradient ◽  
Compressor Stage ◽  
High Pressure Ratio ◽  
Total Pressure Ratio ◽  
Isentropic Efficiency

The pressure ratio of axial compressor stages can be significantly increased by controlling the development of blade and endwall boundary layers in regions of adverse pressure gradient by means of boundary layer suction. This concept is validated and demonstrated through the design and analysis of a unique aspirated compressor stage which achieves a total pressure ratio of 3.5 at a tip speed of 1500 ft/s. The aspirated stage was designed using an axisymmetric through-flow code coupled with a quasi three-dimensional cascade plane code with inverse design capability. Validation of the completed design was carried out with three-dimensional Navier-Stokes calculations. Spanwise slots were used on the rotor and stator suction surfaces to bleed the boundary layer with a total suction requirement of 4% of the inlet mass flow. Additional bleed of 3% was also required on the hub and shroud near shock impingement locations. A three-dimensional viscous evaluation of the design showed good agreement with the quasi three-dimensional design intent, except in the endwall regions. The three-dimensional viscous analysis predicted a mass averaged total pressure ratio of 3.7 at an isentropic efficiency of 93% for the rotor, and a mass averaged total pressure ratio of 3.4 at an isentropic efficiency of 86% for the stage.

scholarly journals Design Methodology for Splittered Axial Compressor Rotors

1990 ◽  
Author(s):  
K.-L. Tzuoo ◽  
S. S. Hingorani ◽  
A. K. Sehra
Keyword(s):  
High Pressure ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Meridional Flow ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Viscous Effects ◽  
High Pressure Ratio ◽  
Rotor Design ◽  
Work Distribution

Recent trend toward lightweight, compact compression systems for advanced aircraft gas turbine engines has created a need for very high pressure ratio fan and compressor stages. One way of achieving pressure ratio in excess of 3:1 in an axial blade row is to introduce splitters (partial vanes) between the principal blades, a concept pioneered by Wennerstrom during early 70s for application in a 3:1 pressure ratio single axial stage. This paper presents an advanced methodology for high pressure ratio splittered rotor design. The methodology centers around combining a meridional flow calculation, an arbitrary meanline blade generation procedure, and 3-D inviscid and viscous analyses. Methods for specifying work distribution, solidity, loss, and deviation distributions, as well as the airfoil generation and splitter vane placement are discussed in detail. Importance of 3-D viscous effects along with results from a 3-D viscous calculation for Wennerstrom’s splittered rotor are also presented.

Turbulence model sensitivity on steady state mapping of a very high pressure ratio compressor stage

2018 ◽  
Author(s):  
Valeriu Drăgan ◽  
Oana Dumitrescu ◽  
Ion Mălael ◽  
Ionuţ Porumbel ◽  
Bogdan Gherman ◽  
...  
Keyword(s):  
High Pressure ◽  
Steady State ◽  
Turbulence Model ◽  
Pressure Ratio ◽  
Compressor Stage ◽  
Model Sensitivity ◽  
High Pressure Ratio ◽  
Very High

Measured and Predicted Performance of a High Pressure Ratio Supersonic Compressor Rotor

2008 ◽  
Author(s):  
Allan D. Grosvenor ◽  
David A. Taylor ◽  
Jonathan R. Bucher ◽  
Michael J. Aarnio ◽  
Paul M. Brown ◽  
...  
Keyword(s):  
Boundary Layer ◽  
High Pressure ◽  
Carbon Capture ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Compression System ◽  
High Pressure Ratio ◽  
Compressor Rotor ◽  
Numerical Predictions ◽  
Shock System

The testing of an 8:1 pressure ratio supersonic single axial compressor rotor referred to as Rampressor-2 is described. Design of this shockwave compression system is based on principles employed for supersonic intakes consisting of a multi-shock compression system and boundary layer treatment. The rotor consists of three blade passages within which the shock system is produced by a ramp, throat and diffuser contoured on the hub. The technology has been previously demonstrated in a 2.3:1 pressure ratio experimental test compressor (Rampressor-1). Measured performance is compared with numerical predictions. Further developments to improve Rampressor performance are discussed, and the appropriateness of this technology for Carbon Capture & Sequestration and LNG applications is highlighted.

scholarly journals The Mach 2 Axial Flow Compressor Stage

1975 ◽  
Author(s):  
F. A. E. Breugelmans
Keyword(s):  
High Pressure ◽  
Guide Vane ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Compressor Stage ◽  
High Pressure Ratio ◽  
Flow Compressor ◽  
Original Configuration

A supersonic compressor stage has been designed for a high pressure ratio at a tip relative inlet Mach number of 2. The stage was operated in the original configuration, but serious inlet stall occurred at part-speed operation. An inlet blockage ring, a bleed system and a variable geometry inlet guide vane have been analyzed and applied to this configuration. The results obtained with the bleed system in the complete stage are presented. The rotor performance is discussed and compared with the stage performance.

Effects of Reynolds number on the performance of a high pressure-ratio turbocharger compressor

2013 ◽  
Vol 56 (6) ◽  
pp. 1361-1369 ◽  
Author(s):  
XinQian Zheng ◽  
Yun Lin ◽  
BinLin Gan ◽  
WeiLin Zhuge ◽  
YangJun Zhang
Keyword(s):  
Reynolds Number ◽  
High Pressure ◽  
Pressure Ratio ◽  
High Pressure Ratio

Effect of Recirculation Device With Counter Swirl Vane on Performance of High Pressure Ratio Centrifugal Compressor

2011 ◽  
Author(s):  
Hideaki Tamaki
Keyword(s):  
High Pressure ◽  
Mach Number ◽  
Flow Rate ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Negative Slope ◽  
Tip Leakage Flow ◽  
Recirculation Flow ◽  
Operating Range ◽  
High Pressure Ratio

Centrifugal compressors used for turbochargers need to achieve a wide operating range. The author has developed a high pressure ratio centrifugal compressor with pressure ratio 5.7 for a marine use turbocharger. In order to enhance operating range, two different types of recirculation devices were applied. One is a conventional recirculation device. The other is a new one. The conventional recirculation device consists of an upstream slot, bleed slot and the annular cavity which connects both slots. The new recirculation device has vanes installed in the cavity. These vanes were designed to provide recirculation flow with negative preswirl at the impeller inlet, a swirl counterwise to the impeller rotational direction. The benefits of the application of both of the recirculation devices were ensured. The new device in particular, shifted surge line to a lower flow rate compared to the conventional device. This paper discusses how the new recirculation device affects the flow field in the above transonic centrifugal compressor by using steady 3-D calculations. Since the conventional recirculation device injects the flow with positive preswirl at the impeller inlet, the major difference between the conventional and new recirculation device is the direction of preswirl that the recirculation flow brings to the impeller inlet. This study focuses on two effects which preswirl of the recirculation flow will generate. (1) Additional work transfer from impeller to fluid. (2) Increase or decrease of relative Mach number. Negative preswirl increases work transfer from the impeller to fluid as the flow rate reduces. It increases negative slope on pressure ratio characteristics. Hence the recirculation flow with negative preswirl will contribute to stability of the compressor. Negative preswirl also increases the relative Mach number at the impeller inlet. It moves shock downstream compared to the conventional recirculation device. It leads to the suppression of the extension of blockage due to the interaction of shock with tip leakage flow.

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