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公开(公告)号:US11199096B1
公开(公告)日:2021-12-14
申请号:US15871323
申请日:2018-01-15
Applicant: United Technologies Corporation
Inventor: Michael Leslie Clyde Papple , David A. Niezelski , Daniel Lecuyer , XingYun Haggard , Domenico Di Florio , Francois Caron , John R. Battye , Panagiota Tsifourdaris , Ghislain Plante , Timothy J. Jennings , Rene Paquet
Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400±10% Hz; a second mode resonance frequency is 4950±10% Hz; a third mode resonance frequency is 7800±10% Hz; a fourth mode resonance frequency is 8700±10% Hz; and a fifth mode resonance frequency is 12500±10% Hz.
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公开(公告)号:US11377965B2
公开(公告)日:2022-07-05
申请号:US15450087
申请日:2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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公开(公告)号:US20170175631A1
公开(公告)日:2017-06-22
申请号:US15450087
申请日:2017-03-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
CPC classification number: F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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