High efficiency, twin spool, radial-high pressure, gas turbine engine

Claim 2

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.

Claim 3

The twin spool gas turbine engine as in claim 1 further including intercooler means associated with said first flow connection means for cooling said pre-compressed air.

Claim 4

The twin spool gas turbine engine as in claim 2 wherein the pressure ratio of said low pressure compressor means is less than or equal to the pressure ratio of said high pressure centrifugal compressor.

Claim 5

The twin spool gas turbine engine as in claim 1 further including recuperator means for extracting heat values from said combustion gases exhausted from said low pressure turbine means and preheating the compressed air delivered from said high pressure centrifugal compressor to said combustion means.

Claim 6

The twin spool gas turbine engine as in claim 1 wherein said first and second flow interconnection means structurally support and orient said low pressure spool spool to be angularly offset from said high pressure spool supplying the external load by about 90°.

Claim 7

The twin spool gas turbine engine as in claim 1 wherein said combustion means includes a low NO x annular combustor having an angled internal cone.

Claim 8

The twin spool gas turbine engine as in claim 1 wherein said low pressure compressor means includes a single entry centrifugal compressor and said low pressure turbine means includes a mixed axial/radial flow turbine.

Claim 9

The twin spool gas turbine engine as in claim 1 wherein said low pressure compressor means includes a single entry centrifugal compressor and said low pressure turbine means includes an axial turbine.

Claim 10

The twin spool gas turbine engine as in claim 1 wherein said low pressure compressor means includes an axial compressor and said low pressure turbine means includes an axial turbine.

Claim 11

The twin spool gas turbine engine as in claim 1 wherein said external load driving means is operatively connected to said high pressure spool shaft means proximate said high pressure centrifugal compressor.

Claim 12

The twin spool gas turbine engine as in claim 1 wherein said first flow interconnecting means includes a manifold for receiving said precompressed air from said low pressure compressor means, said manifold having an increasing cross-sectional area in the flow direction for diffusing the compressed air.

Claim 13

The twin spool gas turbine engine as in claim 1 wherein said second flow interconnecting means includes diffuser means to receive and diffuse partially expanded combustion gases exhausted from said high pressure turbine prior to delivering the gases to said low pressure turbine means.

Claim 14

The twin spool gas turbine engine as in claim 1 further including bleed means associated with said first flow interconnecting means.

Claim 15

The twin spool gas turbine engine as in claim 1 wherein said radial in-flow turbine is sized to directly drive an external load of greater than or equal to about 100 KW and less than or equal to about 1000 KW.

Claim 16

The twin spool gas turbine engine as in claim 1 wherein said radial in-flow turbine is uncooled.

Claim 17

The twin spool gas turbine engine as in claim 1 wherein the expansion ratio across said radial in-flow turbine is greater than the expansion ratio across said low pressure turbine means.

Claim 18

The twin spool gas turbine engine as in claim 1 wherein the overall engine pressure ratio is between about 12/1 and 21/1.

Claim 19

A high efficiency gas turbine engine for direct-driving an external load, the engine comprising: 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.

Claim 20

A high efficiency gas turbine engine for direct-driving an external load, the engine comprising: 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.