High efficiency, twin spool, radial-high pressure, gas turbine engine
First Claim
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1. A high-efficiency, twin spool gas turbine engine for driving an external load, the engine comprising:
- a high pressure spool having shaft means, and a centrifugal compressor and a radial in-flow turbine mounted on said shaft means, said radial in-flow turbine having an expansion ratio of about 4/1 to 8/1;
means connected to said shaft means for driving essentially the entire external load from said high pressure spool shaft means;
combustion means associated with said high pressure spool for receiving compressed air from said centrifugal compressor, for combusting fuel using the compressed air, and for delivering the combustion gases and all the combustion heat energy to said radial in-flow turbine under all engine load conditions;
a low pressure spool having shaft means; and
low pressure compressor means and low pressure turbine means mounted on said low pressure spool shaft means, said low pressure spool being rotatably independent from said high pressure spool and being essentially load-free;
first means for flow interconnecting said low pressure compressor means and said high pressure centrifugal compressor for supplying precompressed air thereto; and
second means for flow interconnecting said high pressure radial in-flow turbine means and said low pressure turbine means for supplying partially expanded combustion gases thereto, wherein the expansion ratio across the radial in-flow turbine is greater than the expansion ratio across the low pressure turbine.
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Abstract
A low cost, low fuel consumption, twin-spool turbine engine with external power take-off essentially exclusively from the high pressure (H.P.) spool uses a radial in-flow turbine and a centrifugal compressor in the H.P. spool and a flow-optimized L.P. spool to achieve pressure ratios above 12/1 for simple cycle engines. Intercooled and recuperated versions are included. The turbine engine according to this invention is ideally suited for applications up to about 1000 KW and will provide some 20% less fuel consumption in this power range compared with conventional designs.
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Citations
18 Claims
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1. A high-efficiency, twin spool gas turbine engine for driving an external load, the engine comprising:
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a high pressure spool having shaft means, and a centrifugal compressor and a radial in-flow turbine mounted on said shaft means, said radial in-flow turbine having an expansion ratio of about 4/1 to 8/1; means connected to said shaft means for driving essentially the entire external load from said high pressure spool shaft means; combustion means associated with said high pressure spool for receiving compressed air from said centrifugal compressor, for combusting fuel using the compressed air, and for delivering the combustion gases and all the combustion heat energy to said radial in-flow turbine under all engine load conditions; a low pressure spool having shaft means; and
low pressure compressor means and low pressure turbine means mounted on said low pressure spool shaft means, said low pressure spool being rotatably independent from said high pressure spool and being essentially load-free;first means for flow interconnecting said low pressure compressor means and said high pressure centrifugal compressor for supplying precompressed air thereto; and second means for flow interconnecting said high pressure radial in-flow turbine means and said low pressure turbine means for supplying partially expanded combustion gases thereto, wherein the expansion ratio across the radial in-flow turbine is greater than the expansion ratio across the low pressure turbine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17)
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18. A high efficiency gas turbine engine for direct-driving an external load, the engine comprising:
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a radial in-flow turbine for operation at a high-peripheral speed, said radial in-flow turbine having an inlet and an outlet; means for supplying high temperature, high pressure gases corresponding to an overall engine pressure ratio greater than about 12/1 to said radial in-flow turbine, said supply means including a low pressure rotating air compressor, a high pressure centrifugal air compressor flow connected to said low pressure rotating air compressor, and means for combusting fuel with compressed air from said high pressure centrifugal air compressor and delivering the combustion gases and all the combustion heat energy to said radial in-flow turbine inlet under all engine load conditions; means for loading said radial in-flow turbine including first shaft means for directly driving both said high pressure centrifugal air compressor and essentially the entire external load by said radial in-flow turbine; and low pressure turbine means for receiving gases from said radial in-flow turbine outlet, for extracting work therefrom, and for driving said low pressure rotating air compressor, said low pressure turbine means including a low pressure turbine and second shaft means directly connecting said low pressure turbine and said low pressure rotating air compressor, wherein said first shaft means and said second shaft means are rotationally independent for providing optimum aerodynamic efficiencies for the respective turbines and compressors associated therewith, thereby providing high engine efficiency, and wherein the expansion ratio across the radial in-flow turbine is greater than the expansion ratio across the low pressure turbine.
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Specification