IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0820722
(2007-06-20)
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등록번호 |
US-7836680
(2011-01-22)
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발명자
/ 주소 |
- Schwarz, Frederick M.
- Glahn, Jorn A.
- Fentress, Brian M.
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출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
3 |
초록
▼
An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force that
An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force that utilizes a coolant for transporting heat generated in the intermittent combustion engine away therefrom and having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. A coupling heat exchanger is coupled to both the gas turbine engine and the intermittent combustion engine to have the engine lubricant and the coolant pass therethrough. A further cooling heat exchanger is coupled to both the coupling heat exchanger and the intermittent combustion engine to have a remote fluid from a source thereof and the coolant pass therethrough.
대표청구항
▼
The invention claimed is: 1. An engine combination for generating forces, the engine system comprising: a gas turbine engine having an air inlet open to the atmosphere, an air compressor, a combustor, a turbine and an exhaust exit nozzle open to the atmosphere all positioned along a fluids flow pat
The invention claimed is: 1. An engine combination for generating forces, the engine system comprising: a gas turbine engine having an air inlet open to the atmosphere, an air compressor, a combustor, a turbine and an exhaust exit nozzle open to the atmosphere all positioned along a fluids flow path passing therethrough for generating force, and utilizing an engine lubricant for lubricating moving components in the gas turbine engine, the air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof; an internal combustion engine provided as an intermittent combustion engine having an air intake coupled to combustion chambers therein and a rotatable output shaft also coupled to those combustion chambers for generating force, and utilizing a coolant for transporting heat generated in the intermittent combustion engine away therefrom, the air transfer duct being connected to the air intake at an opposite end to be capable of transferring compressed air thereto; a coupling heat exchanger coupled to both the gas turbine engine and the intermittent combustion engine as a first coupling subsystem to have the engine lubricant and the coolant pass therethrough to permit the coolant to transport heat in the engine lubricant away therefrom; and a cooling heat exchanger coupled to both the coupling heat exchanger and the intermittent combustion engine as a second coupling subsystem to have a remote fluid from a source thereof and the coolant pass therethrough to permit the remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine. 2. The system of claim 1 wherein the source is a storage tank and the remote fluid is fuel being sent from the storage tank to the gas turbine engine for combustion therein. 3. The system of claim 1 wherein the source is a storage tank and the remote fluid is fuel being sent from the storage tank to the intermittent combustion engine for combustion therein. 4. The system of claim 1 further comprising an aircraft having the engine combination positioned therein and wherein the source is a storage tank and the remote fluid is fuel being sent from the storage tank to a wing tank in a wing of the aircraft for storage therein. 5. The system of claim 1 further comprising an aircraft having the engine combination positioned therein and wherein the source is the gas turbine engine and the remote fluid is air forced by the gas turbine engine to the cooling heat exchanger. 6. The system of claim 1 wherein the cooling heat exchanger is a first cooling heat exchanger, the source is a first source, and the remote fluid is a first remote fluid, and further comprising a second cooling heat exchanger selectively coupled to both the coupling heat exchanger and the intermittent combustion engine as a third coupling subsystem to have a second remote fluid from a second source thereof and the coolant at a selectable rate pass therethrough to permit the second remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine. 7. The system of claim 6 further comprising an aircraft having the engine combination positioned therein and wherein the first source is a storage tank and the first remote fluid is fuel being sent from the storage tank to one of the gas turbine engine and the intermittent combustion engine for combustion therein, and wherein the second source is the gas turbine engine and the second remote fluid is air forced by the gas turbine engine to the second cooling heat exchanger. 8. The system of claim 7 further comprising a third cooling heat exchanger selectively coupled to both the coupling heat exchanger and the intermittent combustion engine as a fourth coupling subsystem to have a third remote fluid from a third source thereof and the coolant at a selectable rate pass therethrough to permit the third remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine. 9. The system of claim 8 wherein the third source is a storage tank and the third remote fluid is fuel being sent from the storage tank to a wing tank in a wing of the aircraft for storage therein. 10. The system of claim 1 further comprising a primary electrical generator having a rotatable input shaft mechanically coupled through a coupler to the intermittent combustion engine output shaft and having an output conductor, the output conductor being electrically energized in response to rotation of the input shaft, and utilizing a generator lubricant for lubricating moving components in the primary electrical generator, and wherein the coupling heat exchanger is a dual coupling heat exchanger coupled to the gas turbine engine, the intermittent combustion engine and the primary electrical generator to have the engine lubricant, the generator lubricant and the coolant pass therethrough to permit the coolant to transport heat in the engine lubricant and in the generator lubricant away therefrom. 11. The system of claim 10 wherein the cooling heat exchanger is a first cooling heat exchanger, the source is a first source, and the remote fluid is a first remote fluid, and further comprising a second cooling heat exchanger selectively coupled to both the dual coupling heat exchanger and the intermittent combustion engine as a third coupling subsystem to have a second remote fluid from a second source thereof and the coolant at a selectable rate pass therethrough to permit the second remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the dual coupling heat exchanger and the intermittent combustion engine. 12. The system of claim 11 further comprising an aircraft having the engine combination positioned therein and wherein the first source is a storage tank and the first remote fluid is fuel being sent from the storage tank to one of the gas turbine engine and the intermittent combustion engine for combustion therein, and wherein the second source is the gas turbine engine and the second remote fluid is air forced by the gas turbine engine to the second cooling heat exchanger. 13. The system of claim 12 further comprising a third cooling heat exchanger selectively coupled to both the dual coupling heat exchanger and the intermittent combustion engine as a fourth coupling subsystem to have a third remote fluid from a third source thereof and the coolant at a selectable rate pass therethrough to permit the third remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the dual coupling heat exchanger and the intermittent combustion engine. 14. The system of claim 13 wherein the third source is a storage tank and the third remote fluid is fuel being sent from the storage tank to a wing tank in a wing of the aircraft for storage therein. 15. The system of claim 1 wherein the coupling heat exchanger is a first coupling heat exchanger and further comprising a primary electrical generator having a rotatable input shaft mechanically coupled through a coupler to the intermittent combustion engine output shaft and having an output conductor, the output conductor being electrically energized in response to rotation of the input shaft, and utilizing a generator lubricant for lubricating moving components in the primary electrical generator, and a second coupling heat exchanger coupled to the first coupling heat exchanger, the intermittent combustion engine and the cooling heat exchanger as a third coupling subsystem to have a the generator lubricant and the coolant pass therethrough to permit the coolant to transport heat in the generator lubricant away therefrom, and with the coolant also circulating through the first coupling heat exchanger, the intermittent combustion engine and the cooling heat exchanger. 16. The system of claim 15 wherein the cooling heat exchanger is a first cooling heat exchanger, the source is a first source, and the remote fluid is a first remote fluid, and further comprising a second cooling heat exchanger selectively coupled to at least one of the first and second coupling heat exchangers and to the intermittent combustion engine as a third coupling subsystem to have a second remote fluid from a second source thereof and the coolant at a selectable rate pass therethrough to permit the second remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the first and second coupling heat exchangers and the intermittent combustion engine. 17. The system of claim 16 further comprising an aircraft having the engine combination positioned therein and wherein the first source is a storage tank and the first remote fluid is fuel being sent from the storage tank to one of the gas turbine engine and the intermittent combustion engine for combustion therein, and wherein the second source is the gas turbine engine and the second remote fluid is air forced by the gas turbine engine to the second cooling heat exchanger. 18. The system of claim 17 further comprising a third cooling heat exchanger selectively coupled to at least one of the first and second coupling heat exchangers and to the intermittent combustion engine as a fourth coupling subsystem to have a third remote fluid from a third source thereof and the coolant at a selectable rate pass therethrough to permit the third remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the first and second coupling heat exchangers and the intermittent combustion engine. 19. The system of claim 18 wherein the third source is a storage tank and the third remote fluid is fuel being sent from the storage tank to a wing tank in a wing of the aircraft for storage therein. 20. A power generation system for propelling, and generating electrical power in, an aircraft, the system comprising: a turbofan engine in an engine compartment in the aircraft with an air inlet in the aircraft open to the atmosphere and leading to an air compressor in the turbofan engine followed by a combustor, and utilizing an engine lubricant for lubricating moving components in the turbofan engine, the air compressor having an air transfer duct extending therefrom so as to be capable of providing compressed air therein and to the combustor; an internal combustion engine provided as an intermittent combustion engine in the aircraft having an air intake coupled to combustion chambers therein, a rotatable output shaft also coupled to those combustion chambers for generating force, and a fuel system for providing fuel to those combustion chambers, and utilizing a coolant for transporting heat generated in the intermittent combustion engine away therefrom, the air transfer duct being connected to the air intake to transfer compressed air thereto; a coupling heat exchanger coupled to both the turbofan engine and the intermittent combustion engine as a first coupling subsystem to have the engine lubricant and the coolant pass therethrough to permit the coolant to transport heat in the engine lubricant away therefrom; and a cooling heat exchanger coupled to both the coupling heat exchanger and the intermittent combustion engine as a second coupling subsystem to have a remote fluid from a source thereof and the coolant pass therethrough to permit the remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine.
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