IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0858319
(2010-08-17)
|
등록번호 |
US-8734085
(2014-05-27)
|
발명자
/ 주소 |
- Lefebvre, Guy
- Durocher, Eric
|
출원인 / 주소 |
- Pratt & Whitney Canada Corp.
|
대리인 / 주소 |
Norton Rose Fulbright Canada LLP
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
19 |
초록
▼
A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial dis
A turbine section of a gas turbine engine is described, which includes an aftmost rotor extending, an aftmost stator located upstream of the aftmost rotor, and a second to last aftmost rotor located upstream of the aftmost stator. The second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator. A turbine exhaust case is located downstream of the aftmost rotor and includes an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor. The turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance that is greater than the first axial distance.
대표청구항
▼
1. A turbine section of a gas turbine engine defining a main gas path extending therethrough, the turbine section comprising: an aftmost rotor extending radially through the main gas path;an aftmost stator extending radially through the main gas path and located upstream of the aftmost rotor;a secon
1. A turbine section of a gas turbine engine defining a main gas path extending therethrough, the turbine section comprising: an aftmost rotor extending radially through the main gas path;an aftmost stator extending radially through the main gas path and located upstream of the aftmost rotor;a second to last aftmost rotor extending radially through the main gas path and located upstream of the aftmost stator, the second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator;a turbine exhaust case located downstream of the aftmost rotor, the turbine exhaust case including an inner radial wall and an outer radial wall defining a main gas path duct downstream of the aftmost rotor, the main gas path duct defining a portion of the main gas path, the turbine exhaust case being axially spaced apart from the aftmost rotor a second axial distance, the second axial distance being greater than the first axial distance; andat least one deformable duct member extending from at least the outer radial wall of the turbine exhaust case, the deformable duct member projecting in an upstream direction towards the aftmost rotor over at least a portion of an axial gap therebetween, the deformable duct member being structurally weaker in an axial direction than in a radial direction, and being substantially frangible when a predetermined maximum axial load is applied thereto, the predetermined maximum axial load being insufficient to deform the turbine exhaust case, such that the deformable duct member is able to absorb an impact force of the aftmost rotor. 2. The turbine section as defined in claim 1, wherein a third axial distance between the aftmost rotor and the aftmost stator is smaller than the second axial distance. 3. The turbine section as defined in claim 1, wherein the deformable duct member at least partially axially overlaps an axially extending aftmost portion of the aftmost rotor. 4. The turbine section as defined in claim 3, wherein the axially extending aftmost portion of the aftmost rotor is a rearwardly extending blade root at a radially inner end of the aftmost rotor. 5. The turbine section as defined in claim 1, wherein the deformable duct member includes at least one of an inner deformable duct member extending from the upstream end of the inner radial wall of the turbine exhaust case and an outer deformable duct member extending from the upstream end of the outer radial wall of the turbine exhaust case. 6. The turbine section as defined in claim 1, wherein the deformable duct member extends substantially axially from the turbine exhaust case. 7. A gas turbine engine comprising: a compressor section, a combustor downstream of the compressor section, a turbine section downstream of the combustor and including a plurality of rotors and a plurality of stators alternately disposed along a main gas path of the gas turbine engine, the plurality of rotors including an aftmost rotor; anda turbine exhaust case disposed downstream of the turbine section, the turbine exhaust case including: an annular outer radial wall located downstream of an aftmost turbine rotor of the turbine section, an annular inner radial wall located downstream of the aftmost turbine rotor of the turbine section, the outer and inner radial walls defining a main gas path duct downstream of the aftmost turbine rotor, the main gas path duct defining therebetween a portion of the main gas path;an outer deformable member extending in an upstream direction from an upstream end of the outer radial wall, the outer deformable member at least partially sealing a first axial gap between the outer radial wall of the turbine exhaust case and the aftmost turbine rotor;an inner deformable member extending in an upstream direction from an upstream end of the inner radial wall, the inner deformable member at least partially sealing a second axial gap between the inner radial wall of the turbine exhaust case and the aftmost turbine rotor; andwherein the outer deformable member and the inner deformable member being structurally weaker in an axial direction than in a radial direction, and the outer and inner deformable members being substantially frangible when a predetermined maximum axial load is applied thereto, the predetermined maximum axial load being insufficient to deform the outer and inner radial walls from which the outer and inner deformable members project, such that the outer and inner deformable members are able to absorb an impact force of the aftmost turbine rotor. 8. The gas turbine engine as defined in claim 7, wherein an aftmost stator is located upstream of the aftmost rotor and a second to last aftmost rotor is located upstream of the aftmost stator, the second to last aftmost rotor being spaced apart a first axial distance from the aftmost stator, and at least one of the outer radial wall and the inner radial wall being spaced apart from the aftmost rotor a second axial distance, the second axial distance being greater than the first axial distance. 9. The gas turbine engine as defined in claim 8, wherein a third axial distance between the aftmost rotor and the aftmost stator is smaller than the second axial distance. 10. The gas turbine engine as defined in claim 7, wherein at least one of the inner deformable members and the outer deformable members axially overlaps a portion of an axially extending aftmost portion of the aftmost rotor. 11. The gas turbine engine as defined in claim 10, wherein the axially extending aftmost portion of the aftmost rotor is a reawardly extending blade root at a radially inner end of the aftmost rotor. 12. The gas turbine engine as defined in claim 7, wherein an aftmost stator is located upstream of the almost rotor and a second to last aftmost rotor is located upstream of the aftmost stator and is spaced apart and separated therefrom by an axial distance, and wherein the axial distance is smaller than both an axial length of the first axial gap and an axial length of the second axial gap. 13. The gas turbine engine as defined in claim 7, wherein at least one of the inner and outer deformable members has a radially extending portion. 14. The gas turbine engine as defined in claim 13, wherein the outer deformable member has the radially extending portion at an upstream end thereof, and the inner deformable portion has the radially extending portion at a downstream end therefore proximate the inner radial wall of the turbine exhaust case.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.