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| 국가/구분 | United States(US) Patent 등록 |
|---|---|
| 국제특허분류(IPC7판) |
|
| 출원번호 | US-0476754 (2012-05-21) |
| 등록번호 | US-9051873 (2015-06-09) |
| 발명자 / 주소 |
|
| 출원인 / 주소 |
|
| 대리인 / 주소 |
|
| 인용정보 | 피인용 횟수 : 0 인용 특허 : 328 |
A metallic-ceramic joint for a turbo-compressor spool is disclosed. A temperature-limited joint is moved from outside the bearings to between the bearings and near the center of the shaft joining the turbine and compressor. This placement can lower the temperature at and around the joint and reduces
A metallic-ceramic joint for a turbo-compressor spool is disclosed. A temperature-limited joint is moved from outside the bearings to between the bearings and near the center of the shaft joining the turbine and compressor. This placement can lower the temperature at and around the joint and reduces the sharp gradient (and associated thermal stress) naturally occurring between the turbine rotor and the cooler joint. The bearing closest to the compressor can be an oil bearing and the bearing closest to the turbine an air bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an oil bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an air bearing. Moving the metallic-ceramic joint between the bearings can provide sufficient isolation to enable the all-air bearing solution.
1. An engine, comprising: a plurality of turbo-compressor spool assemblies, each turbo-compressor spool assembly comprising a compressor and a turbine attached by a common shaft and a first of the turbo-compressor spool assemblies is in fluid communication with a second of the turbo-compressor spool
1. An engine, comprising: a plurality of turbo-compressor spool assemblies, each turbo-compressor spool assembly comprising a compressor and a turbine attached by a common shaft and a first of the turbo-compressor spool assemblies is in fluid communication with a second of the turbo-compressor spool assemblies, at least one of the common shafts of a selected turbo-compressor spool assembly comprising a metallic compressor rotor and a ceramic turbine rotor connected by a metallic-to-ceramic attachment joint and a first bearing being positioned adjacent to the metallic compressor rotor and a second bearing adjacent to the ceramic turbine rotor;a free power turbine driven by a gas flow output by at least one of the turbo-compressor assemblies; anda combustor operable to combust a fuel and a gas output by one of the plurality of turbo-compressor spool assemblies, wherein:when the engine is in operation, the ceramic turbine rotor of the selected turbo-compressor spool assembly operates in a no-failure regime of the ceramic material;the ceramic-to-metallic attachment joint is located on the common shaft of the selected turbo-compressor spool assembly to be in a no-failure regime of the ceramic material, the location of the metallic-to-ceramic attachment joint being positioned between the first and second bearings on the common shaft, andwhen the engine is in operation, the metallic-to-ceramic attachment joint operates at a temperature of no more than about 800° K. 2. The engine of claim 1, wherein the turbine rotor of the selected turbo-compressor spool assembly operates at a temperature of at least about 1,200° K. 3. The engine of claim 1, wherein the first bearing is an oil bearing and the second bearing is an air bearing, and wherein at least one of the following is true: (i) the air and oil are substantially separated by a discourager; and(ii) the air bearing has a larger inside diameter than the oil bearing. 4. The engine of claim 1, wherein the first bearing is an air bearing and the second bearing is an oil bearing. 5. The engine of claim 1, wherein the first and second bearings are air bearings and wherein at least a portion of the air in the air bearing is removed from a gas flow of the compressor of the selected turbo-compressor spool assembly. 6. The engine of claim 5, wherein the air is directed between a labyrinth seal and a discourager and the common shaft. 7. The engine of claim 1, wherein the first and second bearings are oil bearings. 8. The engine of claim 7, wherein air is bled from a compressor air flow and is directed between two labyrinth seals and the common shaft to inhibit oil from leaking into a turbine rotor air flow. 9. The engine of claim 1, wherein a ceramic portion of the common shaft of the selected turbo-compressor spool assembly is at least about 40% of a length of the corresponding common shaft. 10. The engine of claim 1, wherein an outer diameter of a ceramic portion of the common shaft of the selected turbo-compressor spool assembly is substantially the same as an outer diameter of a metallic portion of the common shaft at the joint and wherein the metallic-to-ceramic attachment joint is brazed and comprises a connecting sleeve. 11. The engine of claim 1, wherein an outer diameter of the ceramic portion increases by at least about 20% in proximity to the ceramic turbine rotor while the metallic portion remains substantially constant between the metallic-to-ceramic joint and the metallic compressor rotor. 12. An engine, comprising: a plurality of turbo-compressor spool assemblies, each turbo-compressor spool assembly comprising a compressor and a turbine attached by a common shaft and a first of the turbo-compressor spool assemblies is in fluid communication with a second of the turbo-compressor spool assemblies;a free power turbine driven by a gas flow output by at least one of the turbo-compressor assemblies; anda combustor operable to combust a fuel and a gas output by one of the plurality of turbo-compressor spool assemblies, wherein a selected turbo-compressor spool assembly comprises a metallic compressor rotor and a ceramic turbine rotor connected by a metallic-to-ceramic attachment joint, wherein a first and second bearings are located along a common shaft of the selected turbo-compressor spool assembly, and wherein at least one of the following is true:(i) a turbine rotor of a selected turbo-compressor spool assembly operates in a no-failure regime of the ceramic material and the metallic-to-ceramic attachment joint is located to be in a no-failure regime of the ceramic material;(ii) the metallic-to-ceramic attachment joint is located between the first and second bearings;(iii) a ceramic portion of the common shaft has a length of at least about 40% of a length of the shaft; and(iv) respective diameters of the ceramic portion and a metallic portion of the common shaft are substantially the same in the vicinity of the metallic-to-ceramic attachment joint. 13. The engine of claim 12, wherein (i) is true. 14. The engine of claim 12, wherein (ii) is true. 15. The engine of claim 12, wherein (iii) is true and wherein an outer diameter of a ceramic portion of the common shaft of the selected turbo-compressor spool assembly is substantially the same as an outer diameter of a metallic portion of the common shaft at the joint. 16. The engine of claim 12, wherein (iv) is true. 17. A method, comprising: providing a gas turbine engine, the gas turbine engine comprising a turbo-compressor spool assembly, the turbo-compressor spool assembly comprising a compressor and a turbine attached by a common shaft, a free power turbine driven by a gas flow output by the turbo-compressor assembly, and a combustor operable to combust a fuel and a gas output by the turbo-compressor spool assembly, the compressor comprising a metallic compressor rotor and the turbine comprising a ceramic turbine rotor connected by a metallic-to-ceramic attachment joint; andwhen the gas turbine engine is in operation, maintaining the turbine rotor and the metallic-to-ceramic attachment joint in a no-failure regime of the ceramic material. 18. The method of claim 17, wherein the turbine of the turbo-compressor spool assembly operates at a temperature of at least about 1,200° K and wherein the metallic-to-ceramic attachment joint operates at a temperature of no more than about 800° K. 19. The method of claim 17, wherein a first bearing is positioned adjacent to the metallic compressor rotor and a second bearing is positioned adjacent to the ceramic turbine rotor and wherein the ceramic-to-metallic attachment joint is positioned between first and second bearings on the common shaft of the turbo-compressor spool assembly. 20. The method of claim 19, wherein the first bearing is an oil bearing and the second bearing is an air bearing and wherein the air and oil are substantially separated by a discourager. 21. The method of claim 19, wherein the first bearing is an air bearing and the second bearing is an oil bearing. 22. The method of claim 19, wherein the first and second bearings are air bearings and wherein at least a portion of the air in the air bearing is removed from a gas flow of the compressor of the turbo-compressor spool assembly. 23. The method of claim 22, wherein the air is directed between a labyrinth seal and a discourager and the common shaft. 24. The method of claim 19, wherein the first and second bearings are oil bearings. 25. The method of claim 24, wherein air is bled from a compressor air flow and is directed between two labyrinth seals and the common shaft to inhibit oil from leaking into a turbine rotor air flow. 26. The method of claim 17, wherein a ceramic portion of the common shaft of the turbo-compressor spool assembly is at least about 40% of a length of the common shaft. 27. The method of claim 17, wherein an outer diameter of a ceramic portion of the common shaft of the selected turbo-compressor spool assembly is substantially the same as an outer diameter of a metallic portion of the common shaft at the joint and wherein the metallic-to-ceramic attachment joint is brazed and comprises a connecting sleeve. 28. The method of claim 26, wherein an outer diameter of the ceramic portion increases by at least about 25% in proximity to the ceramic turbine rotor while the metallic portion remains substantially constant between the metallic-to-ceramic joint and the metallic compressor rotor.
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