Development of a High Specific Speed Centrifugal Compressor

1996 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Centrifugal Compressor ◽  
Test Performance ◽  
Pressure Ratio ◽  
High Volume ◽  
Limited Information ◽  
Component Test ◽  
Booster Compressor ◽  
Specific Speed ◽  
Stage Efficiency ◽  
Very High

This paper describes the development of a subscale single stage centrifugal compressor with a dimensionless specific speed (Ns) of 1.8, originally designed for full size appllcatioa as a high volume flow, low pressure ratio, gas booster compressor. The specific stage is noteworthy in that it provides a benchmark representing the performance potential of very high specific speed compressors of which limited information is found in open literature. Stage & component test performance characteristics are presented together with traverse results at the impeller exit. Traverse test results were compared with recent CFD computational predictions, for a exploratory analytical callbration of a very high specific speed impeller geometry. The tested subscale (0.583) compressor essentially satisfied design performance expectations with an overall stage efficiency of 74% incinding, excessive exit casing losses. It was estimated that stage efficiency could be increased to 81% with exit casing losses halved.

Development of a High-Specific-Speed Centrifugal Compressor

1997 ◽  
Vol 119 (3) ◽  
pp. 501-505 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Centrifugal Compressor ◽  
Test Performance ◽  
Pressure Ratio ◽  
High Volume ◽  
Limited Information ◽  
Component Test ◽  
Booster Compressor ◽  
Specific Speed ◽  
Stage Efficiency ◽  
Very High

This paper describes the development of a subscale single-stage centrifugal compressor with a dimensionless specific speed (Ns) of 1.8, originally designed for full-size application as a high volume flow, low pressure ratio, gas booster compressor. The specific stage is noteworthy in that it provides a benchmark representing the performance potential of very high-specific-speed compressors, of which limited information is found in the open literature. Stage and component test performance characteristics are presented together with traverse results at the impeller exit. Traverse test results were compared with recent CFD computational predictions for an exploratory analytical calibration of a very high-specific-speed impeller geometry. The tested subscale (0.583) compressor essentially satisfied design performance expectations with an overall stage efficiency of 74 percent including, excessive exit casing losses. It was estimated that stage efficiency could be increased to 81 percent with exit casing losses halved.

Centrifugal Compressor Blade Trimming for a Range of Flows

2001 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Centrifugal Compressor ◽  
Test Performance ◽  
Pressure Ratio ◽  
Performance Characteristics ◽  
Centrifugal Impeller ◽  
Impeller Blade ◽  
Flow Capacity ◽  
Component Test ◽  
Compressor Performance ◽  
Stage Efficiency

Centrifugal impeller blade trimming has long been used in the turbocharger industry to adapt a single impeller casting to a series of flow capacities, but surprisingly little published literature exists on the effects of trimming to compressor performance. This paper is presented as partial remedy, and describes the performance characteristics of a single stage centrifugal compressor designed and tested to cover a range of flow requirements by impeller blade and diffuser vane trimming. Stage and component test performance characteristics are presented for five trimmed flowpath contours covering a flow capacity range of approximately five to one at a DeLaval number of 0.75. The impeller tip diameter was 356mm, and the highest overall stage efficiency measured was 84.8% at an (air) pressure ratio of 1.5.

Performance Evaluation of Centrifugal Compressor Impellers Using Three-Dimensional Viscous Flow Calculations

1984 ◽  
Vol 106 (2) ◽  
pp. 475-481 ◽  
Author(s):  
J. Moore ◽  
J. G. Moore ◽  
P. H. Timmis
Keyword(s):  
Viscous Flow ◽  
Centrifugal Compressor ◽  
Strong Influence ◽  
Pressure Ratio ◽  
Three Dimensional ◽  
Tip Leakage Flow ◽  
Compression Process ◽  
Tip Leakage ◽  
Low Specific Speed ◽  
Specific Speed

Calculations of three-dimensional viscous flow in the impeller of a centrifugal compressor are used as the basis of a study of the thermodynamics of the compression process. Flow in a high hub-tip ratio low specific speed impeller of approximately 3.4:1 pressure ratio is considered. Results are presented showing the work and loss production processes in the impeller. A strong influence of tip-leakage flow on the performance of this unshrouded wheel is found.

Effect of Impeller-Extended Shrouds on Centrifugal Compressor Performance as a Function of Specific Speed

1983 ◽  
Vol 105 (3) ◽  
pp. 457-465 ◽  
Author(s):  
L. Sapiro
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Centrifugal Compressors ◽  
Gas Compression ◽  
Blade Tip ◽  
Compressor Performance ◽  
The Subject ◽  
Specific Speed ◽  
Vaneless Diffusers ◽  
Outside Diameter

Centrifugal compressors for gas compression applications usually employ low-pressure ratio, backward-swept impellers with vaneless diffusers. To increase the compressor flow range and speed, impeller blades are occasionally trimmed, resulting in an extended shroud configuration. The effect of extended front and back impeller shrouds on the performance of centrifugal compressors with vaneless diffusers, and the variation of this effect as a function of specific speed, is thus of concern and is the subject of this paper. An investigation was carried out on two backward-swept shrouded impellers of common blade tip and inducer hub diameters, but different inducer tip diameters (corresponding to low and high specific speeds), with the front and back shrouds extending 20 percent above the blade’s outside diameter.

Effect of Impeller Extended Shrouds on Centrifugal Compressor Performance as a Function of Specific Speed

1982 ◽  
Author(s):  
L. Sapiro
Keyword(s):  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Centrifugal Compressors ◽  
Gas Compression ◽  
Blade Tip ◽  
Compressor Performance ◽  
The Subject ◽  
Specific Speed ◽  
Vaneless Diffusers ◽  
Outside Diameter

Centrifugal compressors for gas compression applications usually employ low-pressure ratio, backward-swept impellers with vaneless diffusers. To increase the compressor flow range and speed, impeller blades are occasionally trimmed, resulting in an extended shroud configuration. The effect of extended front and back impeller shrouds on the performance of centrifugal compressors with vaneless diffusers, and the variation of this effect as a function of specific speed, is thus of concern and is the subject of this paper. An investigation was carried out on two backward-swept shrouded impellers of common blade tip and inducer hub diameters, but different inducer tip diameters (corresponding to low and high specific speeds), with the front and back shrouds extending 20 percent above the blade’s outside diameter.

Conceptual Design of a Centrifugal Compressor Including Consideration of the Effect of Inlet Prewhirl

1992 ◽  
Author(s):  
A. Whitfield
Keyword(s):  
Conceptual Design ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Design Procedure ◽  
Outer Radius ◽  
Compressor Design ◽  
Dimensional Parameters ◽  
Specific Speed ◽  
Impeller Geometry

A non-dimensional impeller design procedure, including the effect of inlet prewhirl, is described. It is shown that the basic non-dimensional parameters commonly used to present the performance of compressors also provide an adequate basis from which a conceptual design procedure can be developed. The adoption of composite non-dimensional groupings such as specific speed and specific diameter are unnecessary. The design procedure is developed non-dimensionally to provide the appropriate impeller geometry as a ratio of the outer radius, and inlet and discharge blade angles. A compressor design for a pressure ratio of 4 to 1 is used to provide an illustrative example.

An Experimental Investigation on the Clocking Effect Between Inlet Guide Vanes and Vaned Diffuser in a Centrifugal Compressor Stage

2008 ◽  
Author(s):  
Jiang Hua ◽  
Xi Guang ◽  
Zhang Wei ◽  
WuQi Gong ◽  
ZhiHeng Wang
Keyword(s):  
Experimental Investigation ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Centrifugal Impeller ◽  
Vaned Diffuser ◽  
Guide Vanes ◽  
Inlet Guide Vanes ◽  
Stage Efficiency ◽  
Peak Value

Different circumferential angle positions between stator or rotor vane rows in turbomachinery can lead to different flow structures or stage performances. The clocking effect phenomenon has been detected in axial compressor and turbine by investigators, but rarely reported on centrifugal compressor. The present work is an experimental investigation on the stator clocking effect between inlet guide vanes (IGV) and vaned diffuser in a low-speed centrifugal compressor. The experimental rig consists of a circumferentially rotatable IGV, an unshrouded centrifugal impeller, a vaned diffuser, a volute and etc. The impeller diameter is 796mm, and the rotate speed is about 3100 rpm. At each inlet prewhirl angle of −20°, 0° and +20°, the stage performance curves are measured at three clocking angle positions of 0°, 8° and 16°. The result shows that at the circumferential angles of 0° and 8°, the efficiency curve has a double peak value feature, but at the angle of 16° being the conventional single peak value curve. Further, at the circumferential angles of 0° and 8°, the stage efficiency is bigger 3.6% than that case of the angle being 16°, where the IGV prewhirl angles are 0° and 20°. When the IGV prewhirl angle is changed into −20°, the stage efficiency increases about 2.0% near the first peak value position at the circumferential angles of 0°and 8° than at 16°, however, at the second peak value position, the stage efficiency at the circumferential angle of 0° is bigger about 1.4% than at 8° and 16°. Moreover, the circumferential angle positions between IGV and vaned diffuser have corresponding influence on the pressure ratio.

Design of a Centrifugal Compressor With Low Specific Speed for Automotive Fuel Cell

2008 ◽  
Author(s):  
Xinqian Zheng ◽  
Yangjun Zhang ◽  
Hong He ◽  
Zhiling Qiu
Keyword(s):  
Fuel Cell ◽  
Centrifugal Compressor ◽  
Electric Motor ◽  
High Speed ◽  
High Efficiency ◽  
Pressure Ratio ◽  
System A ◽  
Automotive Fuel ◽  
Low Specific Speed ◽  
Specific Speed

Centrifugal compressors driven by electric motor are the promising type for fuel cell pressurization system. A low specific speed centrifugal compressor powered by an ordinary high-speed (about 25,000rpm) electric motor has been designed at Tsinghua University for automotive fuel cell engines. The experimental results indicate that the designed low specific speed centrifugal compressor has comparatively high efficiency and wide operating range. In the condition of designed speed (24,000rpm), the highest efficiency and pressure ratio of the centrifugal compressor is up to 70% and 1.6, respectively. The designed low specific speed centrifugal compressor can meet the requirement of air systems of automotive fuel cell engines preliminarily. Moreover, the low specific speed centrifugal compressor avoids difficulties of usage of ultra-high-speed electric motors (about 60,000rpm) in high specific speed compressor. Based on the preliminary results of this centrifugal compressor, a new low specific speed centrifugal compressor with higher performances is being developed.

scholarly journals New Radial Engine Technology From Kongsburg

1983 ◽  
Author(s):  
R. J. Mowill ◽  
S. Strom
Keyword(s):  
High Performance ◽  
Pressure Ratio ◽  
Extensive Experience ◽  
High Pressure Ratio ◽  
New Family ◽  
Radial Turbine ◽  
Specific Speed ◽  
Radial Turbines ◽  
Novel Design ◽  
Very High

The first engine of a new family of high performance, rugged radial turbines is presented. The new single shaft 1500 kW site rated KG3 is built upon extensive experience from the field proven KG2 of the same nominal power. The KG3 is being developed both as a simple cycle and recuperated engine providing specific fuel consumptions in the range of 0.29 to 0.19 kg/kW·hr (0.47 to 0.32 lbs/hp·hr). The new Kongsberg engine makes use of a high specific speed high pressure ratio centrifugal compressor combined with a very high tip speed uncooled radial turbine to obtain optimized aerodynamic matching. Several novel design features are described.

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