Microcircuit cooling for gas turbine engine combustor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/00
F23R-003/04
F23R-003/12
F23R-003/06
F23R-003/14
F02C-007/12
출원번호
US-0644227
(2015-03-11)
등록번호
US-10094563
(2018-10-09)
발명자
/ 주소
Cunha, Frank J.
Snyder, Timothy S.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
35
초록▼
A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includ
A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.
대표청구항▼
1. A combustor component of a gas turbine engine, comprising: a bulkhead heat shield panel defining a bend and a microcircuit flow path within a thickness of said bulkhead heat shield panel; andwherein said microcircuit flow path includes a first elongated section and a second, distinct elongated se
1. A combustor component of a gas turbine engine, comprising: a bulkhead heat shield panel defining a bend and a microcircuit flow path within a thickness of said bulkhead heat shield panel; andwherein said microcircuit flow path includes a first elongated section and a second, distinct elongated section, said first elongated section having an inlet and said second elongated section having an outlet radially outward of the inlet, said first and second sections connected at said bend, said microcircuit flow path at said bend being positioned radially between said inlet and said outlet, said microcircuit flow path follows said bend such that the microcircuit flow path is generally circular in cross section, and said outlet is configured to eject flow impinging on a forward heat shield panel defining a combustion chamber; andwherein said bulkhead heat shield panel extends between a forward end and an aft end and said outlet extends through said aft end. 2. The combustor component as recited in claim 1, further comprising a support shell, said bulkhead heat shield panel mounted to said support shell. 3. The combustor component as recited in claim 2, further comprising a combustor case, said support shell mounted to said combustor case. 4. The combustor component as recited in claim 1, wherein said bulkhead heat shield panel is generally planar. 5. The combustor component as recited in claim 1, wherein said bulkhead heat shield panel defines a fuel injector aperture. 6. The combustor component as recited in claim 1, wherein said forward heat shield panel includes a multiple of internal features. 7. The combustor component as recited in claim 6, wherein said multiple of internal features repeat tangentially and axially throughout said forward heat shield panel. 8. The combustor component as recited in claim 6, further comprising a wall depression located on a hot side of said forward heat shield panel downstream of said outlet and spaced from said microcircuit flow path, said wall depression configured to provide film wall attachment of flow communicated from said outlet onto said hot side. 9. The combustor component as recited in claim 6, wherein said multiple of internal features include a pair of islands configured to meter flow. 10. A combustor component of a gas turbine engine, comprising: a bulkhead heat shield panel defining a combustion chamber, said bulkhead heat shield panel defining a bend and a microcircuit flow path within a thickness of said bulkhead heat shield panel; andwherein said microcircuit flow path includes a first elongated section and a second, distinct elongated section, said first elongated section having an inlet and said second elongated section having an outlet, said first and second sections connected at said bend, said microcircuit flow path at said bend being positioned radially between said inlet and said outlet, said microcircuit flow path follows said bend such that the microcircuit flow path is generally circular in cross section, and said outlet is configured to eject flow impinging on a second heat shield panel defining said combustion chamber; andwherein said bulkhead heat shield panel extends between a forward end and an aft end and said outlet extends through said aft end. 11. The combustor component as recited in claim 10, wherein said bend is radially outward of said inlet. 12. The combustor component as recited in claim 10, wherein said bulkhead heat shield panel defines a fuel injector aperture radially inward of said inlet. 13. A method of cooling a combustor of a gas turbine engine comprising: providing a first heat shield panel defining a microcircuit flow path;communicating a cooling flow through a bend defined by said microcircuit flow path;wherein said microcircuit flow path includes an inlet and an outlet radially outward of said inlet, said microcircuit flow path at said bend being positioned radially between said inlet and said outlet;communicating the cooling flow through a flow swirler in communication with said microcircuit flow path and with a diffusion flow, said diffusion flow communicated from an annular passageway between a combustor case and said first heat shield panel; andejecting flow from said flow swirler in a tangential direction with respect to an axial flow path and to a combustion chamber defined by said first heat shield panel. 14. The method as recited in claim 13, further comprising ejecting airflow from a bulkhead heat shield panel impinge on said first heat shield panel. 15. The method as recited in claim 13, further comprising a wall depression located on a hot side of said first heat shield panel. 16. The combustor component as recited in claim 1, wherein said bend being defined such that in-plane re-circulating flows are established in response to communication of cooling flow through said microcircuit flow path. 17. The combustor component as recited in claim 16, wherein said bulkhead heat shield panel and said forward heat shield panel are separate and distinct. 18. The combustor component as recited in claim 10, wherein said bend being defined such that in-plane re-circulating flows are established in response to communication of cooling flow through said microcircuit flow path, and said bulkhead heat shield panel and said second heat shield panel are separate and distinct. 19. The method as recited in claim 13, wherein said step of communicating the cooling flow through said bend includes establishing in-plane re-circulating flows in said microcircuit flow path. 20. The combustor component as recited in claim 9, wherein said pair of islands include opposed walls that converge to define a metering section, and said opposed walls diverge downstream of said metering section.
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이 특허에 인용된 특허 (35)
Cunha, Francisco J.; Pietraszkiewicz, Edward F., Airfoil cooling with staggered refractory metal core microcircuits.
Burd, Steven W.; Cheung, Albert K.; Dempsey, Dae K.; Hoke, James B.; Kramer, Stephen K.; Ols, John T.; Smith, Reid Dyer Curtis; Sowa, William A., Gas turbine combustor.
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