IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0762970
(2013-02-08)
|
등록번호 |
US-8511061
(2013-08-20)
|
발명자
/ 주소 |
- Merry, Brian D.
- Suciu, Gabriel L
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
Carlson, Gaskey & Olds, P.C.
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
11 |
초록
▼
A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate ca
A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.
대표청구항
▼
1. A gas turbine engine comprising: a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path;a shaft supporting a compressor section that is arranged axially between the inlet case flow path and the intermedi
1. A gas turbine engine comprising: a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path;a shaft supporting a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path, wherein the shaft includes a main shaft and a flex shaft having bellows, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end;a geared architecture coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture, wherein the geared architecture includes a sun gear supported on the second end;a first bearing supporting the shaft relative to the intermediate case; anda second bearing supporting the shaft relative to the inlet case, and the second bearing is arranged radially outward from the flex shaft. 2. The gas turbine engine according to claim 1, wherein the shaft includes a hub secured to the main shaft, and the compressor section includes a rotor mounted to the hub, the hub supporting the second bearing. 3. The gas turbine engine according to claim 2, wherein the inlet case includes an inlet case portion defining the inlet case flow path, and a bearing support portion removably secured to the inlet case portion, the second bearing mounted to the bearing support portion. 4. The gas turbine engine according to claim 1, wherein the inlet case includes a first inlet case portion defining the inlet case flow path, and a bearing support portion removably secured to the inlet case portion, the second bearing mounted to the bearing support portion. 5. The gas turbine engine according to claim 1, wherein the intermediate case includes an intermediate case portion defining the intermediate case flow path, and a bearing support portion removably secured to the intermediate case portion, the first bearing mounted to the bearing support portion. 6. The gas turbine engine according to claim 1, wherein the first bearing is a ball bearing and the second bearing is a roller bearing. 7. The gas turbine engine according to claim 1, wherein the first and second bearings are arranged in separate sealed lubrication compartments. 8. The gas turbine engine according to claim 1, comprising a lubrication compartment, the second bearing and the geared architecture arranged in the lubrication compartment. 9. A gas turbine engine comprising: a core housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path;a shaft supporting a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path, wherein the compressor section includes a variable stator vane array;a first bearing supporting the shaft relative to the intermediate case;a second bearing supporting the shaft relative to the inlet case, and the second bearing is axially aligned with and radially inward of the variable stator vane array, the first and second bearings are arranged in separate sealed lubrication compartments; anda geared architecture coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture, wherein the shaft includes a main shaft and a flex shaft having bellows, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end, wherein the geared architecture includes a sun gear supported on the second end, and the second bearing is arranged radially outward from the flex shaft, wherein the shaft includes a hub secured to the main shaft, and the compressor section includes a rotor mounted to the hub, the hub supporting the second bearing. 10. A gas turbine engine comprising: a core housing providing a core flow path;a fan;a shaft supporting a compressor section arranged within the core flow path, wherein the compressor section is fluidly connected to the fan, the compressor section comprising a first pressure compressor and a second pressure compressor upstream from the first pressure compressor, the second pressure compressor including multiple compressor stages; andfirst and second bearings supporting the shaft relative to the core housing and are arranged radially inward of and axially overlapping with at least some of the multiple compressor stages;a geared architecture coupled to the shaft, and the fan coupled to and rotationally driven by the geared architecture, wherein the shaft includes a main shaft and a flex shaft having bellows, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end, wherein the geared architecture includes a sun gear supported on the second end, and the second bearing is arranged radially outward from the flex shaft; andwherein the gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than about six (6). 11. The gas turbine engine according to claim 10, further comprising: a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising:a high pressure turbine; anda low pressure turbine. 12. The gas turbine engine according to claim 10, wherein the core housing includes a first inlet case portion defining an inlet case flow path, and a bearing support portion removably secured to the inlet case portion, the second bearing mounted to the bearing support portion. 13. The gas turbine engine according to claim 10, wherein the core housing includes an intermediate case portion defining an intermediate case flow path, and a bearing support portion removably secured to the intermediate case portion, the first bearing mounted to the bearing support portion. 14. The gas turbine engine according to claim 10, wherein the multiple compressor stages includes a variable stator vane array, rotatable compressor blades, and a fixed stator vane array. 15. A gas turbine engine comprising: a core housing providing a core flow path;a fan;a shaft supporting a compressor section arranged within the core flow path, wherein the compressor section is fluidly connected to the fan, the compressor section comprising a first pressure compressor and a second pressure compressor upstream from the first pressure compressor, the second pressure compressor including multiple compressor stages; and first and second bearings supporting the shaft relative to the core housing and being arrangedradially inward of and axially overlapping with at least some of the multiple compressor stages a combustor fluidly connected to the compressor section;a turbine section fluidly connected to the combustor, the turbine section comprising: a high pressure turbine; a low pressure turbine;a geared architecture coupled to the shaft, and the fan coupled to and rotationally driven by the geared architecture, wherein the shaft includes a main shaft and a flex shaft having bellows, the flex shaft secured to the main shaft at a first end and including a second end opposite the first end, wherein the geared architecture includes a sun gear supported on the second end, and the second bearing is arranged radially outward from the flex shaft; andwherein the gas turbine engine includes at least one of a low Fan Pressure Ratio of less than about 1.45 and a low pressure turbine pressure ratio that is greater than about 5.
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