公开(公告)号：US10801342B2

公开(公告)日：2020-10-13

申请号：US14644596

申请日：2015-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark David Ring ,  Scot A Webb ,  Mark J Rogers ,  Gerald D Cassella ,  Charles H Warner ,  Eric A Kuehne ,  Jonathan J Earl ,  Matthew M Zietala ,  Neil L Tatman ,  Randall J Butcher ,  Matthew R Willett ,  Nicholas R Leslie

IPC: F01D9/04 ,  F01D25/24

Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to the second end-of-cluster vane at an interface that includes an angled load interface therebetween; and a multiple of base vanes between the first end-of-cluster vane and the neighbor vane, the angled load interface different than an interface between each of the multiple of base vane.

公开(公告)号：US10774651B1

公开(公告)日：2020-09-15

申请号：US15869124

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopolous ,  Lisa I. Brilliant

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/28 ,  F01D5/34

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506±10% Hz, a second mode with a frequency of 1732±10% Hz, a third mode with a frequency of 2268±10% Hz, a fourth mode with a frequency of 4007±10% Hz, a fifth mode with a frequency of 4851±10% Hz and a sixth mode with a frequency of 6416±10% Hz.

公开(公告)号：US10718223B1

公开(公告)日：2020-07-21

申请号：US15867820

申请日：2018-01-11

Applicant: United Technologies Corporation

Inventor： Charles H. Warner ,  William R. Edwards ,  Mark David Ring ,  Sean Nolan ,  Ernest D. Casparie

IPC: F01D9/04 ,  F01D5/00 ,  F01D5/14

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.13-1.23 inch (28.7-31.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634±10% Hz, a second mode with a frequency of 5611±10% Hz, a third mode with a frequency of 19027±10% Hz, a fourth mode with a frequency of 29268±10% Hz, a fifth mode with a frequency of 33103±10% Hz, a sixth mode with a frequency of 34908±10% Hz and a seventh mode with a frequency of 41277±10% Hz.

公开(公告)号：US09334756B2

公开(公告)日：2016-05-10

申请号：US13656906

申请日：2012-10-22

Applicant: United Technologies Corporation

Inventor： Mark David Ring ,  David Cassella ,  Jonathan Earl ,  Eric Kuehne ,  Charles Warner

IPC: F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D25/246 ,  F01D5/32 ,  F01D9/041 ,  F01D9/042 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/90 ,  Y10T29/49323

Abstract: An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.

Abstract translation: 一种组件包括多个叶片，前向衬垫段和后衬层段。 前部衬垫段和后部衬套段安装到多个叶片上，并且每个段包括长度小于360°的弧。

公开(公告)号：US11236616B1

公开(公告)日：2022-02-01

申请号：US15868499

申请日：2018-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopoulos ,  Kate Hudon ,  John Joseph Papalia

IPC: F01D5/16 ,  F02C3/06 ,  F04D29/32 ,  F04D29/38 ,  F04D29/66 ,  F02K3/06

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.

公开(公告)号：US10815785B1

公开(公告)日：2020-10-27

申请号：US15869119

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kurt R. Heinemann ,  Sumin Tao ,  Christopher B. Jelks ,  Xuedong Zhou ,  Mark David Ring ,  Konstantinos Panagiotis Giannakopoulos ,  Kate Hudon ,  John Joseph Papalia

IPC: F01D5/16 ,  F01D5/14 ,  F01D5/30

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.

公开(公告)号：US10677266B1

公开(公告)日：2020-06-09

申请号：US15869939

申请日：2018-01-12

Applicant: United Technologies Corporation

Inventor： Charles H. Warner ,  William R. Edwards ,  Mark David Ring ,  Sean Nolan ,  Ernest D. Casparie

IPC: F04D29/66 ,  F01D9/02 ,  F01D25/04 ,  F04D29/54 ,  F02C3/06 ,  F02K3/06

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.63-0.73 inch (16.0-18.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852±10% Hz, a second mode with a frequency of 11917±10% Hz, a third mode with a frequency of 30842±10% Hz and a fourth mode with a frequency of 35225±10% Hz.

公开(公告)号：US10287919B2

公开(公告)日：2019-05-14

申请号：US14431820

申请日：2013-02-19

Applicant: United Technologies Corporation

Inventor： Mark David Ring ,  Jonathan Earl ,  Eric Kuehne

IPC: F01D25/24 ,  F01D5/32 ,  F01D9/04 ,  F01D11/00

Abstract: An assembly includes a first vane pack, a second vane pack, and a liner lock segment. The first vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack is disposed to abut the first vane pack. The liner lock segment is disposed between the first vane pack and the second vane pack.

公开(公告)号：US20150292342A1

公开(公告)日：2015-10-15

申请号：US14644596

申请日：2015-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark David Ring ,  Scot A. Webb ,  Mark J. Rogers ,  Gerald D. Cassella ,  Charles H. Warner ,  Eric A. Kuehne ,  Jonathan J. Earl ,  Matthew M. Zietala ,  Neil L. Tatman ,  Randall J. Butcher ,  Matthew R. Willett ,  Nicholas R. Leslie

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/61 ,  F05D2240/12 ,  F05D2240/80 ,  Y02T50/672

Abstract: A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to said second end-of-cluster vane; and a multiple of base vanes between said first end-of-cluster vane and said neighbor vane.

Abstract translation: 用于燃气涡轮发动机的叶片组包括第一端簇叶片，第二端簇叶片，与所述第二端簇叶片相邻的相邻叶片; 以及在所述第一端部叶片叶片和所述相邻叶片之间的多个基部叶片。

公开(公告)号：US20140093363A1

公开(公告)日：2014-04-03

申请号：US13656906

申请日：2012-10-22

Applicant: United Technologies Corporation

Inventor： Mark David Ring ,  David Cassella ,  Jonathan Earl ,  Eric Kuehne ,  Charles Warner

IPC: F01D9/04

CPC classification number: F01D25/246 ,  F01D5/32 ,  F01D9/041 ,  F01D9/042 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/90 ,  Y10T29/49323

Abstract: An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.

Abstract translation: 组件包括多个叶片，前向衬垫段和后衬层段。 前部衬垫段和后部衬套段安装到多个叶片上，并且每个段包括长度小于360°的弧。