Transportation propulsion system
First Claim
Patent Images
1. A gas turbine engine comprising:
- at least one gas generator and a power turbine arranged to drive a propulsion output shaft, said gas generator including coupled gas compressors and turbines;
said gas generator generating a first stream of high pressure gas at a high temperature high pressure and a second stream of low pressure gas at a low temperature; and
a wave rotor convertor between said gas generator and said power turbine receiving said first and second streams of gas from said gas generator, said wave rotor combining said first and second streams of gas into a third stream of high pressure gas of an intermediate temperature intermediate the temperatures of said first and second streams of gas;
said third stream of gas being directed from said wave rotor convertor to said power turbine for driving said power turbine and propulsion output shaft.
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Abstract
A gas turbine engine (8) has a plurality of gas generators (28, 30, 32, 34) which generate and cool pressurized gas streams (38, 40) that are combined in a high efficiency topping cycle in a wave rotor convertor (36). The output of the wave rotor convertor (36) drives a single power turbine (24). Each gas generator may comprise an aircraft-type turbofan engine (28B, 30B). An electric generator (48) is selectively driven by each gas generator (28, 30, 32, 34).
18 Citations
11 Claims
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1. A gas turbine engine comprising:
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at least one gas generator and a power turbine arranged to drive a propulsion output shaft, said gas generator including coupled gas compressors and turbines; said gas generator generating a first stream of high pressure gas at a high temperature high pressure and a second stream of low pressure gas at a low temperature; and a wave rotor convertor between said gas generator and said power turbine receiving said first and second streams of gas from said gas generator, said wave rotor combining said first and second streams of gas into a third stream of high pressure gas of an intermediate temperature intermediate the temperatures of said first and second streams of gas; said third stream of gas being directed from said wave rotor convertor to said power turbine for driving said power turbine and propulsion output shaft. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A gas turbine engine comprising:
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a plurality of gas generators for supplying high pressure high temperature gas to a power turbine arranged to drive a propulsion output shaft, each gas generator including coupled gas compressors and turbines; each of said gas generators generating a first stream of high pressure gas at a high temperature high pressure and a second stream of low pressure gas at a low temperature; said first and second streams of gas being combined into a third stream of high pressure gas of an intermediate temperature intermediate the temperatures of said first and second streams of gas;
said third stream of gas being directed to said power turbine for driving said power turbine and propulsion output shaft; andeach of said gas generators being selectively operated. - View Dependent Claims (9, 10, 11)
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Specification