IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0008308
(2012-03-15)
|
등록번호 |
US-9200983
(2015-12-01)
|
국제출원번호 |
PCT/US2012/029231
(2012-03-15)
|
§371/§102 date |
20131113
(20131113)
|
국제공개번호 |
WO2012/134824
(2012-10-04)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Florida Turbine Technologies, Inc.
|
대리인 / 주소 |
Christopher & Weisberg, P.A.
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
11 |
초록
▼
A system and a process for testing a gas turbine engine or component thereof, especially for a large aero gas turbine engine, and for a process for testing a large industrial gas turbine engine that requires large flow capacity and pressure ratios. The system and process may include the use of a lar
A system and a process for testing a gas turbine engine or component thereof, especially for a large aero gas turbine engine, and for a process for testing a large industrial gas turbine engine that requires large flow capacity and pressure ratios. The system and process may include the use of a large compressed air storage reservoir to provide compressed air to the testing system. Further, the system and process may also include the use of a pre-heating system, which may include a heater and a heat exchange device, to warm the compressed air from the compressed air storage reservoir to a temperature suitable to simulate normal operating conditions of the gas turbine engine or component thereof.
대표청구항
▼
1. A process for testing a component of a gas turbine engine, comprising: providing a component for testing, the test component being one of a full annular combustor, a high Mach number aero engine, a high Mach number aero vehicle, a turbine connected in its non-operating condition, or an afterburne
1. A process for testing a component of a gas turbine engine, comprising: providing a component for testing, the test component being one of a full annular combustor, a high Mach number aero engine, a high Mach number aero vehicle, a turbine connected in its non-operating condition, or an afterburner of an aero engine;providing at least one compressed air reservoir having a total volume of at least 10,000 m3;placing the test component in fluid communication with the at least one compressed air reservoir;providing a heating device upstream of the test component and downstream of the compressed air reservoir, the heating device increasing a temperature of compressed air from the compressed air reservoir; anddirecting the compressed air from the compressed air reservoir through the heating device and into the test component. 2. The process of claim 1, wherein the test component is at least one of a gas turbine engine, a combustor, a compressor, and a turbine. 3. The process of claim 1, wherein the heating device heats the compressed air from the compressed air reservoir to a temperature of between approximately 300° C. and approximately 900 ° C. before the compressed air enters the test component. 4. The process of claim 1, further comprising: providing a heat exchange device having a first flow path and a second flow path, the first flow path and second flow path being in thermal communication with each other;directing compressed air from the compressed air reservoir into the first flow path;directing compressed air from the first flow path to test component; anddirecting compressed air from the test component to the second flow path. 5. The process of claim 4, further comprising: providing a heater upstream of the test component;directing compressed air from the first flow path to the heater;directing compressed air from the heater to the test component; anddirecting compressed air from the test component to the second flow path. 6. The process of claim 5, wherein the heater and heat exchange device heat the compressed air from the compressed air reservoir to a temperature of between approximately 300 ° C. and approximately 900 ° C. before the compressed air enters the test component. 7. The process of claim 1, wherein the heating device is at least one of an electric heater, a plurality of electric heaters arranged in series, a gas-powered heater, a plurality of gas-powered heaters arranged in series, a heat exchange device, a thermal storage device, and a high pressure combustion heater. 8. The process of claim 1, further comprising: providing an air compressor downstream of the test component;operating the test component, the test component providing energy to the compressor to produce compressed air; andstoring the compressed air in the at least one compressed air reservoir. 9. The process of claim 8, wherein the compressed air has a pressure of between approximately 10 bars to approximately 200 bars. 10. The process of claim 1, wherein the at least one compressed air reservoir comprises a low pressure compressed air reservoir, a medium pressure compressed air reservoir, and a high pressure compressed air reservoir. 11. The process of claim 10, further comprising: driving a low pressure compressor with the test component to produce a low pressure compressed air, the compressed air having a pressure of between approximately 10 bars to approximately 20 bars;driving a medium pressure compressor with the test component to produce a medium pressure compressed air, the compressed air having a pressure of between approximately 20 bars to approximately 50 bars; anddriving a high pressure compressor with the test component to produce a high pressure compressed air, the compressed air having a pressure of between approximately 50 bars to approximately 200 bars; andstoring the low pressure compressed air in the low pressure compressed air reservoir, storing the medium pressure compressed air in the medium pressure compressed air reservoir, and storing the high pressure compressed air in the high pressure compressed air reservoir. 12. The process of claim 11, further comprising: using the low pressure compressed air to test a test component under low pressure conditions;using the medium pressure compressed air to test a test component under medium pressure conditions; andusing the high pressure compressed air to test a test component under high pressure conditions. 13. The process of claim 1, wherein the heating device is an energy-fed, non-vitiating heating device, the energy fed to the non-vitiating heating device being one of fossil fuel and electricity. 14. A testing facility for a test component, the testing facility comprising: one or more compressed air reservoirs having a total volume of approximately 10,000 m3 to approximately 1,000,000 m3;one or more air flow paths in fluid communication with the one or more compressed air reservoirs;an energy-fed, non-vitiating heating device downstream of the one or more compressed air reservoirs being in thermal communication with at least one air flow path and upstream of the test component, the energy fed to the non-vitiating heating device being one of fossil fuel and electricity, the non-vitiating heating device increasing a temperature of compressed air from the one or more compressed air reservoirs; andthe test component being one of a full annular combustor, a high Mach number aero engine, a high Mach number aero vehicle, a turbine connected in its non-operating condition, and an afterburner of an aero engine. 15. The testing facility of claim 14, further comprising: a testing chamber having a first end and a second end, the first end being in fluid communication with the compressed air storage reservoir;a vacuum chamber in fluid communication with the second end of the testing chamber; anda vacuum pump in fluid communication with the vacuum chamber,wherein a directional air flow is generated in the testing chamber from the first end to the second end from at least one of the vacuum chamber and the compressed air reservoir. 16. The testing facility of claim 14, wherein the compressed air reservoir contains at least some compressed air, the heating device heating the compressed air from the compressed air reservoir in at least one air flow path to a temperature of between approximately 300 ° C. and approximately 900 ° C. 17. The testing facility of claim 14, further comprising: a heat exchange device having a first flow path and a second flow path, the first flow path and the second flow path being in thermal communication with each other, and the first flow path being upstream of the heating device and the second flow path being downstream of the heating device. 18. The testing facility of claim 17, wherein the compressed air reservoir contains at least some compressed air, the heating device and heat exchange device heating the compressed air from the compressed air reservoir in at least one air flow path to a temperature of between approximately 300 ° C. and approximately 900 ° C. 19. The testing facility of claim 14, wherein the heating device is at least one of an electric heater, a plurality of electric heaters arranged in series, a gas-powered heater, a plurality of gas-powered heaters arranged in series, a heat exchange device, a thermal storage device, and a high pressure combustion heater. 20. The testing facility of claim 14, wherein the one or more compressed air reservoirs is an underground plenum. 21. The testing facility of claim 14, further comprising: a low pressure compressor producing low pressure compressed air having a pressure of between approximately 10 bars and 20 bars;a medium pressure compressor producing medium pressure compressed air having a pressure of between approximately 20 bars and approximately 50 bars; anda high pressure compressor producing high pressure compressed air having a pressure of between approximately 50 bars and approximately 200 bars,the one or more compressed air reservoirs including: a low pressure compressed air reservoir in fluid communication with the low pressure compressor;a medium pressure compressed air reservoir in fluid communication with the medium pressure compressor; anda high pressure compressed air reservoir in fluid communication with the high pressure compressor. 22. A testing facility for a test component, the testing facility comprising: a test component, the test component having an optimal operating temperature, the test component being one of a full annular combustor, a high Mach number aero engine, a high Mach number aero vehicle, a turbine connected in its non-operating condition, and an afterburner of an aero engine;at least one compressed air reservoir having a total volume of at least 10,000 m3, at least a portion of the volume containing compressed air;a heating device upstream of the test component and downstream of the at least one compressed air reservoir, the heating device increasing a temperature of compressed air from the at least one compressed air reservoir; anda heat exchange device having a first flow path and a second flow path, the first flow path and the second flow path being in thermal communication with each other, the first flow path being upstream of the heating device and the second flow path being downstream of the heating device;the heat exchange device heating compressed air from the compressed air reservoir to a temperature of between approximately 300 ° C. and approximately 900 ° C., andthe heating device further heating the compressed air from the first flow path when the heat exchange device heats the compressed air to a temperature less than the optimal operating temperature of the test component. 23. A testing facility for a large frame gas turbine engine or components thereof, the testing facility comprising: a plurality of compressed air reservoirs having a total volume of approximately 10,000 m3 to approximately 1,000,000 m3, the plurality of compressed air reservoirs including: a low pressure compressed air reservoir in fluid communication with the low pressure compressor;a medium pressure compressed air reservoir in fluid communication with the medium pressure compressor; anda high pressure compressed air reservoir in fluid communication with the high pressure compressor;a plurality of air flow paths in fluid communication with the plurality of compressed air reservoirs;a heating device downstream of the one or more compressed air reservoirs being in thermal communication with at least one air flow path;a low pressure compressor producing low pressure compressed air having a pressure of between approximately 10 bars and 20 bars;a medium pressure compressor producing medium pressure compressed air having a pressure of between approximately 20 bars and approximately 50 bars; anda high pressure compressor producing high pressure compressed air having a pressure of between approximately 50 bars and approximately 200 bars.
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