An Advanced Radial-Component Industrial Turbine Engine

1983 ◽  
Vol 105 (4) ◽  
pp. 947-952
Author(s):  
J. Mowill ◽  
S. Strom
Keyword(s):  
High Performance ◽  
Pressure Ratio ◽  
Radial Component ◽  
Extensive Experience ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
New Family ◽  
Radial Turbines ◽  
Novel Design ◽  
Very High

The first engine of a new family of high performance, industrial 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 0.29–0.19 kg/kW-hr (0.47–0.32 lbs/hp-hr). This 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.

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.

scholarly journals The Design and Evaluation of a High Pressure Ratio Radial Turbine

1992 ◽  
Author(s):  
K. R. Pullen ◽  
N. C. Baines ◽  
S. H. Hill
Keyword(s):  
High Pressure ◽  
High Speed ◽  
Pressure Ratio ◽  
Performance Measurements ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Turbine Efficiency ◽  
Wide Range ◽  
Dimensional Parameters ◽  
Very High

A single stage, high speed, high pressure ratio radial inflow turbine was designed for a single shaft gas turbine engine in the 200 kW power range. A model turbine has been tested in a cold rig facility with correct simulation of the important non-dimensional parameters. Performance measurements over a wide range of operation were made, together with extensive volute and exhaust traverses, so that gas velocities and incidence and deviation angles could be deduced. The turbine efficiency was lower than expected at all but the lowest speed. The rotor incidence and exit swirl angles, as obtained from the rig test data, were very similar to the design assumptions. However, evidence was found of a region of separation in the nozzle vane passages, presumably caused by a very high curvature in the endwall just upstream of the vane leading edges. The effects of such a separation are shown to be consistent with the observed performance.

Quick Start of an Industrial Gas Turbine Engine Through the Development of “Silent Start” VGV Schedule

2020 ◽  
Author(s):  
Senthil Krishnababu ◽  
Vili Panov ◽  
Simon Jackson ◽  
Andrew Dawson
Keyword(s):  
Guide Vane ◽  
Pressure Ratio ◽  
Axial Compressor ◽  
Rotating Stall ◽  
Rotor Blades ◽  
Start Time ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Compressor Map ◽  
Industrial Gas Turbine

Abstract In this paper, research that was carried out to optimise an initial variable guide vane schedule of a high-pressure ratio, multistage axial compressor is reported. The research was carried out on an extensively instrumented scaled compressor rig. The compressor rig tests carried out employing the initial schedule identified regions in the low speed area of the compressor map that developed rotating stall. Rotating stall regions that caused undesirable non-synchronous vibration of rotor blades were identified. The variable guide vane schedule optimisation carried out balancing the aerodynamic, aero-mechanical and blade dynamic characteristics gave the ‘Silent Start’ variable guide vane schedule, that prevented the development of rotating stall in the start regime and removed the non-synchronous vibration. Aerodynamic performance and aero-mechanical characteristics of the compressor when operated with the initial schedule and the optimised ‘Silent Start’ schedule are compared. The compressor with the ‘Silent Start’ variable guide vane schedule when used on a twin shaft engine reduced the start time to minimum load by a factor of four and significantly improved the operability of the engine compared to when the initial schedule was used.

Design, Test and Analysis of a High-Pressure-Ratio Transonic Fan

2003 ◽  
Author(s):  
W. John Calvert ◽  
Paul R. Emmerson ◽  
Jon M. Moore
Keyword(s):  
High Performance ◽  
Mechanical Design ◽  
Pressure Ratio ◽  
Operating Conditions ◽  
Pressure Transducers ◽  
Technology Acquisition ◽  
Laser Anemometry ◽  
High Pressure Ratio ◽  
Response Pressure ◽  
Stage Matching

Aircraft gas turbine engines require compression systems with high performance and low weight and cost. There is therefore a continuing drive to increase compressor stage pressure ratios, particularly for military fans. To meet this need, a technology acquisition programme has been carried out by QinetiQ and Rolls-Royce. Firstly, the stage matching issues for an advanced two-stage military fan were investigated, including the effects of employing variable inlet guide vanes. From this, the requirements for the first stage together with key operating conditions for the blading were defined. The blade profiles were then designed to satisfy the range of aerodynamic conditions using a quasi-3D calculation system. A satisfactory compromise between the aerodynamic and mechanical design requirements was reached in which a blisk construction was employed for the rotor, machined from a single piece of titanium. The new stage was manufactured and tested successfully, and it achieved its target flow, pressure ratio and efficiency on the first build. Detailed measurements of the internal flows using laser anemometry and high response pressure transducers were taken. Finally, these data have been analysed and used to calibrate current 3D multi-row CFD methods.

Process Applications and Design of Single and Two Shaft Hot Gas Expander Compression Systems

1973 ◽  
Vol 95 (4) ◽  
pp. 1076-1082
Author(s):  
H. D. Linhardt
Keyword(s):  
High Pressure ◽  
Steam Turbine ◽  
High Performance ◽  
Pressure Ratio ◽  
Direct Result ◽  
Low Speed ◽  
High Pressure Ratio ◽  
Hot Gas ◽  
Recent Advances ◽  
Radial Inflow Turbine

Single and two shaft hot gas expander compression systems will soon replace conventional multitrain, low speed equipment due to significant economic and process advantages. The single train concept is a direct result of the recent advances in high pressure ratio compressor, high performance radial inflow turbine and high performance steam turbine technology. The application and custom engineering of single train compression systems is discussed, whereby emphasis is placed on performance and reliability.

Design and Test of a Small, High Pressure Ratio Radial Turbine

1996 ◽  
Vol 118 (2) ◽  
pp. 362-370 ◽  
Author(s):  
A. C. Jones
Keyword(s):  
Power Systems ◽  
Pressure Ratio ◽  
Expansion Ratio ◽  
Turbine Engine ◽  
High Pressure Ratio ◽  
Turbine Efficiency ◽  
Auxiliary Power ◽  
Minimal Modification ◽  
Power Application ◽  
Consumption Goals

This paper describes the aerodynamic design and rig test of a radial inflow turbine having a rotor tip diameter of 4.58 inches. The single-stage turbine was designed for use in the Sundstrand Power Systems (SPS) T-100 Multipurpose Small Power Unit (MPSPU). The T-100 is a small, single-shaft, simple-cycle gas turbine engine intended for airborne, vehicular, and ground-based auxiliary power application. Nominal power output of the engine is 50 hp, with growth capability to 100 hp with minimal modification. Aggressive specific fuel consumption goals for the engine led to a demanding turbine efficiency target of 87 percent total to static, referred to exhaust diffuser exit, at an expansion ratio of 5.7:1 and a flow rate of 0.73 lb/s. Details of the design approach are given, together with test results from the turbodrive rig. The results include overall stage mapping and rotor exit surveys.

A New 1.7MW Industrial Gas Turbine: The Ruston Hurricane

1991 ◽  
Author(s):  
A. T. Sanders ◽  
M. H. Tothill ◽  
G. R. Wood
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Thermodynamic Efficiency ◽  
The Novel ◽  
Exhaust Temperature ◽  
High Pressure Ratio ◽  
Industrial Gas Turbine ◽  
Novel Design

The paper describes the design of a compact new 1.7MW (2300hp) single shaft industrial gas turbine and package, with high efficiency and exhaust temperature ideal for industrial congeneration applications. These advantages are obtained with a high pressure ratio single stage centrifugal compressor, single high temperature combustor and two-stage axial flow turbine using only one row of cooled blades. The novel design features are described with the associated development testing. A typical installation is also described showing the potential for very high overall thermodynamic efficiency.

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
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