Airfoil fluid curtain to mitigate or prevent flow path leakage
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-011/04
F01D-009/04
F01D-025/12
F01D-025/00
F02C-003/14
출원번호
US-0426354
(2017-02-07)
등록번호
US-10253643
(2019-04-09)
발명자
/ 주소
Kerns, Daniel Patrick
Reynolds, Brandon ALlanson
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
35
초록▼
Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes com
Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
대표청구항▼
1. A flow path assembly of a gas turbine engine, the flow path assembly comprising: an inner wall defining an inner boundary of a flow path, the inner wall further defining a plurality of pockets therein;a unitary outer wall defining an outer boundary of the flow path, the unitary outer wall includi
1. A flow path assembly of a gas turbine engine, the flow path assembly comprising: an inner wall defining an inner boundary of a flow path, the inner wall further defining a plurality of pockets therein;a unitary outer wall defining an outer boundary of the flow path, the unitary outer wall including a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine, the combustor portion and the turbine portion being integrally formed as a single unitary structure; anda plurality of nozzle airfoils, each nozzle airfoil of the plurality of nozzle airfoils having an inner end radially opposite an outer end, each nozzle airfoil of the plurality of nozzle airfoils defining an internal cavity for receipt of a flow of cooling fluid,wherein the turbine portion comprises an outer band of a nozzle portion of the first turbine stage,a shroud of a blade portion of the first turbine stage,an outer band of a nozzle portion of the second turbine stage, anda shroud of a blade portion of the second turbine stage,wherein the inner end of each nozzle airfoil of the plurality of nozzle airfoils is received in one of the plurality of pockets defined in the inner wall,wherein the outer end of each nozzle airfoil of the plurality of nozzle airfoils defines an inlet for the flow of cooling fluid to flow into the internal cavity,wherein the inner end of each nozzle airfoil of the plurality of nozzle airfoils defines an outlet for the flow of cooling fluid to flow from the internal cavity to the one of the plurality of pockets, andwherein the flow of cooling fluid flowing from the outlet of each nozzle airfoil of the plurality of nozzle airfoils forms a fluid curtain to discourage fluid leakage from the flow path. 2. The flow path assembly of claim 1, wherein the unitary outer wall defines a plurality of openings therethrough, and wherein each of the plurality of openings is configured for receipt of one of the plurality of nozzle airfoils. 3. The flow path assembly of claim 2, wherein the outer end of each nozzle airfoil of the plurality of nozzle airfoils is positioned in one opening of the plurality of openings in the unitary outer wall when the inner end of the nozzle airfoil of the plurality of nozzle airfoils is received in the one of the pockets defined in the inner wall. 4. The flow path assembly of claim 1, further comprising a plurality of seals, wherein one seal of the plurality of seals is positioned in each one of the plurality of pockets between the inner end of the nozzle airfoil received in the one of the plurality of pockets and the inner wall. 5. The flow path assembly of claim 1, wherein a fluid flows through the flow path at a flow path pressure, and wherein the flow of cooling fluid is pressurized above the flow path pressure. 6. The flow path assembly of claim 1, wherein at least one of the inlet and the outlet is sized to meter the flow of cooling fluid from the internal cavity to the one of the plurality of pockets. 7. The flow path assembly of claim 1, wherein the combustor portion and the turbine portion are integrally formed from a ceramic matrix composite (CMC) material such that the unitary outer wall is a CMC component, and wherein the inner wall is formed from a CMC material such that the inner wall is a CMC component. 8. A flow path assembly of a gas turbine engine, the flow path assembly comprising: an inner wall defining an inner boundary of a flow path, the inner wall further defining a plurality of pockets therein;a unitary outer wall defining an outer boundary of the flow path, the unitary outer wall including a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine, the combustor portion and the turbine portion being integrally formed as a single unitary structure; anda plurality of nozzle airfoils, each nozzle airfoil of the plurality of nozzle airfoils having an inner end radially opposite an outer end, the inner end of each nozzle airfoil of the plurality of nozzle airfoils received in one of the plurality of pockets defined in the inner wall,wherein the turbine portion comprises an outer band of a nozzle portion of the first turbine stage,a shroud of a blade portion of the first turbine stage,an outer band of a nozzle portion of the second turbine stage, anda shroud of a blade portion of the second turbine stage, andwherein a flow of cooling fluid is directed into each respective pocket of the plurality of pockets, the flow of cooling fluid forming a fluid curtain to discourage fluid leakage from the flow path into the respective pocket. 9. The flow path assembly of claim 8, wherein each nozzle airfoil of the plurality of nozzle airfoils defines an internal cavity for receipt of the flow of cooling fluid to direct into each respective pocket. 10. The flow path assembly of claim 9, wherein the inner end of each nozzle airfoil of the plurality of nozzle airfoils defines an outlet to direct the flow of cooling fluid from the internal cavity to the respective pocket. 11. The flow path assembly of claim 8, wherein a plurality of apertures are defined in the inner wall, each aperture of the plurality of apertures defined from an outer surface of the inner wall to one respective pocket of the plurality of pockets. 12. The flow path assembly of claim 11, wherein the flow of cooling fluid is directed through each aperture to the one respective pocket of the plurality of pockets. 13. The flow path assembly of claim 8, wherein the fluid curtain is formed along an outer surface of each nozzle airfoil of the plurality of nozzle airfoils. 14. The flow path assembly of claim 8, wherein a plurality of openings are defined in the unitary outer wall, and wherein each of the plurality of nozzle airfoils are inserted through the unitary outer wall and into respective ones of the plurality of pockets in the inner wall such that the outer end of each nozzle airfoil of the plurality of nozzle airfoils is positioned in one of the plurality of openings. 15. A flow path assembly of a gas turbine engine, the flow path assembly comprising: an inner wall defining an inner boundary of a flow path;a unitary outer wall defining an outer boundary of the flow path, the unitary outer wall including a combustor portion extending through a combustion section of the gas turbine engine and a turbine portion extending through at least a first turbine stage and a second turbine stage of a turbine section of the gas turbine engine, the combustor portion and the turbine portion being integrally formed as a single unitary structure, the unitary outer wall defining a plurality of pockets therein; anda plurality of nozzle airfoils, each nozzle airfoil of the plurality of nozzle airfoils having an inner end radially opposite an outer end, the outer end of each nozzle airfoil of the plurality of nozzle airfoils received in one of the plurality of pockets defined in the unitary outer wall,wherein the turbine portion comprises an outer band of a nozzle portion of the first turbine stage,a shroud of a blade portion of the first turbine stage,an outer band of a nozzle portion of the second turbine stage, anda shroud of a blade portion of the second turbine stage, andwherein a flow of cooling fluid is directed into each respective pocket of the plurality of pockets, the flow of cooling fluid forming a fluid curtain to discourage fluid leakage from the flow path into the respective pocket. 16. The flow path assembly of claim 15, wherein each nozzle airfoil of the plurality of nozzle airfoils defines an internal cavity for receipt of the flow of cooling fluid to direct into each respective pocket. 17. The flow path assembly of claim 16, wherein the outer end of each nozzle airfoil of the plurality of nozzle airfoils defines an outlet to direct the flow of cooling fluid from the internal cavity to the respective pocket. 18. The flow path assembly of claim 15, wherein a plurality of apertures are defined in the unitary outer wall, each aperture of the plurality of apertures defined from an outer surface of the unitary outer wall to one respective pocket of the plurality of pockets. 19. The flow path assembly of claim 18, wherein the flow of cooling fluid is directed through each aperture to the one respective pocket of the plurality of pockets. 20. The flow path assembly of claim 15, wherein the fluid curtain is formed along an outer surface of each nozzle airfoil of the plurality of nozzle airfoils.
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