IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0343019
(2008-12-23)
|
등록번호 |
US-8087249
(2012-01-03)
|
발명자
/ 주소 |
- Ottaviano, Marcus Joseph
- Parks, Robert John
- Noon, John Lawrence
- D'Andrea, Mark Michael
- Regan, Thomas Michael
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
16 인용 특허 :
10 |
초록
▼
A gas turbine engine turbine cooling system includes an impeller and a diffuser directly downstream of the impeller, a bleed for bleeding clean cooling air from downstream of the diffuser, and one or more channels in fluid communication with the bleed. Each of the channels having a generally radiall
A gas turbine engine turbine cooling system includes an impeller and a diffuser directly downstream of the impeller, a bleed for bleeding clean cooling air from downstream of the diffuser, and one or more channels in fluid communication with the bleed. Each of the channels having a generally radially extending section followed by a generally axially aftwardly extending section terminating at an annular cooling air plenum connected to accelerators. The radially and axially aftwardly extending sections may be connected by a bend section of the cooling air channel and the axially aftwardly extending section may be angled radially inwardly going from the bend section to the cooling air plenum. Each of the cooling channels includes an inner wall formed by a forward end wall extending radially outwardly from an inner combustor casing, an annular cover covering a radially inner portion of the forward end wall, and the inner combustor casing.
대표청구항
▼
1. A gas turbine engine turbine cooling system comprising: an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one
1. A gas turbine engine turbine cooling system comprising: an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one or more channels in fluid communication with the cooling air bleed means, each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section,the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators, anda generally axially aftwardly extending section of each of the one or more channels terminating at an aft conical section including cooling air apertures of an inner combustor casing diverging outwardly with respect to an engine centerline and disposed between the one or more channels and the annular cooling air plenum. 2. A system as claimed in claim 1, further comprising the cooling air bleed means including an annular manifold in fluid communication with the bleed location downstream of an outlet of the diffuser. 3. A system as claimed in claim 2, further comprising the bleed location located downstream of an outlet of the diffuser. 4. A system as claimed in claim 1, further comprising the generally radially and axially aftwardly extending sections being connected by a bend section of the cooling air channel and the generally axially aftwardly extending section being angled radially inwardly going from the bend section to the cooling air plenum. 5. A system as claimed in claim 4, further comprising the cooling air bleed means including an annular manifold in fluid communication with the bleed location downstream of an outlet of the diffuser. 6. A system as claimed in claim 5, further comprising the bleed location located where compressor discharge pressure air enters a deswirl cascade along an internal radius portion of the deswirl cascade. 7. A gas turbine engine turbine cooling system comprising: an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one or more channels in fluid communication with the cooling air bleed means, each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section,the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators,an annular combustor stator assembly including a radially extending forward end wall extending radially outwardly from and joined to an inner combustor casing,a radially outer portion of the forward end wall being an aft wall of the diffuser,a stator plenum disposed between and in fluid communication with the impeller and an annular cavity extending radially between the inner combustor casing and the high pressure rotor and extending axially between forward and aft thrust balance seals,the stator plenum being bounded by a radially inner portion of the forward end wall and an annular cover spaced axially aftwardly of the radially inner portion of the forward end wall, andeach of the cooling channels having a channel inner wall running along a radially outer portion of the forward end wall, the annular cover, and the inner combustor casing. 8. A system as claimed in claim 7, further comprising: the annular cover including a cover aft wall having a planar annular wall section followed by a conical wall section,circumferentially spaced apart channel side walls extending outwardly from and attached to the channel inner wall, anda channel outer wall spaced outwardly from the channel inner wall and attached to the channel side walls. 9. A system as claimed in claim 8, further comprising each of the cooling channels terminating at an aft conical section of the inner combustor casing between the annular cooling air plenum and the cooling channels and cooling air apertures disposed through the aft conical section between the annular cooling air plenum and the cooling channels. 10. A gas turbine engine turbine cooling system comprising: an annular centrifugal compressor impeller of a high pressure rotor and a diffuser directly downstream of the impeller,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one or more channels in fluid communication with the cooling air bleed means, each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section,the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators,the generally radially and axially aftwardly extending sections being connected by a bend section of the cooling air channel and the generally axially aftwardly extending section being angled radially inwardly going from the bend section to the cooling air plenum,an annular combustor stator assembly including a radially extending forward end wall extending radially outwardly from and joined to an inner combustor casing,a radially outer portion of the forward end wall being an aft wall of the diffuser,a stator plenum disposed between and in fluid communication with the impeller and an annular cavity extending radially between the inner combustor casing and the high pressure rotor and extending axially between forward and aft thrust balance seals,the stator plenum being bounded by a radially inner portion of the forward end wall and an annular cover spaced axially aftwardly of the radially inner portion of the forward end wall, andeach of the cooling channels having a channel inner wall formed by and running along a radially outer portion of the forward end wall, the annular cover, and the inner combustor casing. 11. A system as claimed in claim 10, further comprising: the annular cover including a cover aft wall having a planar annular wall section followed by a conical wall section,circumferentially spaced apart channel side walls extending outwardly from the channel inner wall, anda channel outer wall spaced outwardly from the channel inner wall and attached to the channel side walls. 12. A system as claimed in claim 11, further comprising each of the cooling channels terminating at an aft conical section of the inner combustor casing between the annular cooling air plenum and the cooling channels and cooling air apertures disposed through the aft conical section between the annular cooling air plenum and the cooling channels. 13. A gas turbine engine assembly comprising: a combustor between a high pressure compressor and a high pressure turbine,a high pressure rotor including a centrifugal compressor having an annular centrifugal compressor impeller directly adjacent to and downstream of a diffuser,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one or more channels in fluid communication with the cooling air bleed means,each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section,the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators, anda generally axially aftwardly extending section of each of the one or more channels terminating at an aft conical section including cooling air apertures of an inner combustor casing diverging outwardly with respect to an engine centerline and disposed between the one or more channels and the annular cooling air plenum. 14. A gas turbine engine assembly comprising: a combustor between a high pressure compressor and a high pressure turbine,a high pressure rotor including a centrifugal compressor having an annular centrifugal compressor impeller directly adjacent to and downstream of a diffuser,a cooling air bleed means for bleeding clean cooling air from a bleed location downstream of an outlet of the diffuser,one or more channels in fluid communication with the cooling air bleed means, each of the one or more channels having a generally radially extending section followed by a generally axially aftwardly extending section,the one or more channels terminating at and in fluid communication with an annular cooling air plenum having one or more accelerators,an annular combustor stator assembly including a forward end wall extending radially outwardly from and joined to an inner combustor casing,a radially outer portion of the forward end wall being an aft wall of the diffuser,a stator plenum disposed between and in fluid communication with the impeller and an annular cavity extending radially between the inner combustor casing and the high pressure rotor and extending axially between forward and aft thrust balance seals, andthe stator plenum being in part bounded by a radially inner portion of the forward end wall. 15. An engine assembly as claimed in claim 14, further comprising the cooling air bleed means including an annular manifold in fluid communication with the bleed location downstream of an outlet of the diffuser. 16. An engine assembly as claimed in claim 15, further comprising the bleed location located where compressor discharge pressure air enters a deswirl cascade along an internal radius portion of the deswirl cascade. 17. An engine assembly claimed in claim 14, further comprising: an annular combustor stator assembly including a radially extending forward end wall extending radially outwardly from and joined to an inner combustor casing,a radially outer portion of the forward end wall being an aft wall of the diffuser,a stator plenum disposed between and in fluid communication with the impeller and the annular cavity,the stator plenum being bounded by a radially inner portion of the forward end wall and an annular cover spaced axially aftwardly of the radially inner portion of the forward end wall, andeach of the cooling channels having a channel inner wall formed by and running along a radially outer portion of the forward end wall, the annular cover, and the inner combustor casing. 18. An engine as claimed in claim 17, further comprising: the annular cover including a cover aft wall having a planar annular wall section followed by a conical wall section,circumferentially spaced apart channel side walls extending outwardly from the channel inner wall, anda channel outer wall spaced outwardly from the channel inner wall and attached to the channel side walls. 19. An engine as claimed in claim 18, further comprising each of the cooling channels terminating at an aft conical section of the inner combustor casing between the annular cooling air plenum and the cooling channels and cooling air apertures disposed through the aft conical section between the annular cooling air plenum and the cooling channels. 20. An engine as claimed in claim 18, further comprising the cooling air bleed means including an annular manifold in fluid communication with the bleed location downstream of an outlet of the diffuser. 21. An engine as claimed in claim 20, further comprising the bleed location located where compressor discharge pressure air enters a deswirl cascade along an internal radius portion of the deswirl cascade. 22. An engine as claimed in claim 14, further comprising the generally radially and axially aftwardly extending sections being connected by a bend section of the cooling air channel and the generally axially aftwardly extending section being angled radially inwardly going from the bend section to the cooling air plenum. 23. An engine as claimed in claim 22, further comprising: an annular combustor stator assembly including a radially extending forward end wall extending radially outwardly from and joined to an inner combustor casing,a radially outer portion of the forward end wall being an aft wall of the diffuser,a stator plenum disposed between and in fluid communication with the impeller and the annular cavity,the stator plenum being bounded by a radially inner portion of the forward end wall and an annular cover spaced axially aftwardly of the radially inner portion of the forward end wall, andeach of the cooling channels having a channel inner wall formed by and running along a radially outer portion of the forward end wall, the annular cover, and the inner combustor casing. 24. An engine as claimed in claim 23, further comprising: the annular cover including a cover aft wall having a planar annular wall section followed by a conical wall section,circumferentially spaced apart channel side walls extending outwardly from the channel inner wall, anda channel outer wall spaced outwardly from the channel inner wall and attached to the channel side walls. 25. An engine as claimed in claim 24, further comprising each of the cooling channels terminating at an aft conical section of the inner combustor casing between the annular cooling air plenum and the cooling channels and cooling air apertures disposed through the aft conical section between the annular cooling air plenum and the cooling channels.
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