Turbine blade with mate face cooling air flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/10
F01D-011/00
F01D-005/22
출원번호
US-0048634
(2011-03-15)
등록번호
US-8951014
(2015-02-10)
발명자
/ 주소
Corcoran, Christopher
Thomen, Seth J.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
O'Shea Getz P.C.
인용정보
피인용 횟수 :
2인용 특허 :
20
초록▼
A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstre
A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel.
대표청구항▼
1. A gas turbine engine blade assemblage, comprising: a dovetail;a shank extending from the dovetail;an airfoil;a platform between the shank and the airfoil, the platform comprising a sidewall extending between an upstream side and a downstream side of the platform, wherein a first pin channel exten
1. A gas turbine engine blade assemblage, comprising: a dovetail;a shank extending from the dovetail;an airfoil;a platform between the shank and the airfoil, the platform comprising a sidewall extending between an upstream side and a downstream side of the platform, wherein a first pin channel extends from and through the upstream side of the sidewall, wherein a second pin channel extends from and through the downstream side of the sidewall, wherein the first and second pin channels are co-axial, and wherein the first pin channel includes a radial notch at an upstream longitudinal end of the first pin channel, and the second pin channel is at least partially formed by a second pedestal surface that is substantially planar and extends to and through the sidewall at the downstream side of the platform; anda pin within the first and second pin channels, wherein the pin includes a radial projection that sits within the notch. 2. The assemblage of claim 1, wherein the notch comprises a straight surface substantially parallel to the first and second pin channels, and an arcuate surface. 3. The assemblage of claim 1, wherein the pin comprises: a first longitudinal end region;a second longitudinal end region;a reduced cross sectional area region; andwherein the reduced cross sectional area region is separated from the first longitudinal end region by a first main body region and the reduced cross sectional area region is separated from the second longitudinal end region by a second main body region, wherein a cross sectional area of the reduced cross sectional area region is less than a cross sectional area of each of the first and second main body regions, and wherein the reduced cross sectional area region is concentric with the first and second main body regions. 4. The assemblage of claim 3, wherein the radial projection extends from a longitudinal end of the first longitudinal end region. 5. The assemblage of claim 1, wherein the pin comprises: a first longitudinal end region that sits within the first pin channel;a second longitudinal end region that sits within the second pin channel;a longitudinal slit radially extending through the pin; andwherein the slit is separated from the first longitudinal end region by a first main body region and the slit is separated from the second longitudinal end region by a second main body region. 6. The assemblage of claim 5, wherein the radial projection extends from a longitudinal exterior of the first longitudinal end region. 7. The assemblage of claim 6, wherein the first and second main body regions are cylindrical. 8. The assemblage of claim 1, where the pin comprises: a first longitudinal end region;a second longitudinal end region;an undercut region; andwherein the undercut region is separated from the first longitudinal end region by a first main body region and the undercut region is separated from the second longitudinal end region by a second main body region, wherein the undercut region is undercut with respect to the first and second main body regions, and wherein the radial projection extends from a longitudinal end of the first longitudinal end region. 9. The assemblage of claim 8, wherein the pin is formed from a metal alloy selected from the group consisting of IN100, IN718, IN625, and INCONEL X-750. 10. The assemblage of claim 8, wherein the first and second main body regions are cylindrical. 11. The assemblage of claim 8, wherein the undercut region is formed by a continuous helical cut about a surface of the undercut region that allows cooling air to flow along opposite surfaces of the pin.
Benjamin, Edward Durell; Butkiewicz, Jeffrey John; Honkomp, Mark Steven; Wassynger, Stephen Paul; Fernandez, Emilio; Collado, Carlos Alberto, Methods and apparatus for cooling gas turbine engine rotor assemblies.
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