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

IPC: F01D5/28 ,  F01D5/16 ,  F01D5/14 ,  F01D5/18

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.

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

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C7/12 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

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.

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

IPC: F02C7/12 ,  F01D9/04 ,  F04D29/58 ,  F04D29/32 ,  F04D29/54 ,  F01D5/18 ,  F01D25/12

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.