公开(公告)号：US20180112876A1

公开(公告)日：2018-04-26

申请号：US15334860

申请日：2016-10-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Kevin Zacchera ,  Brian T. Hazel ,  William F. Werkheiser

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/00018 ,  F23R2900/03044 ,  Y02T50/675 ,  Y02T50/6765

Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused gate blended into a hot side of the liner panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused gate blended into a hot side of the liner panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused gate tangentially cast into a hot side of a liner panel; and applying a thermal barrier coating to the hot side of the liner panel over the remnants of the radiused gate.

公开(公告)号：US09926797B2

公开(公告)日：2018-03-27

申请号：US14603126

申请日：2015-01-22

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Jonathan Lemoine ,  Kevin Zacchera

IPC: F01D11/00 ,  F01D25/12 ,  F01D25/16 ,  F02C3/10

CPC classification number: F01D11/005 ,  F01D25/125 ,  F01D25/162 ,  F02C3/10 ,  Y02T50/675

Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.

公开(公告)号：US09885254B2

公开(公告)日：2018-02-06

申请号：US14695323

申请日：2015-04-24

Applicant: United Technologies Corporation

Inventor： Jeffrey J. Lienau ,  Dustin W. Davis ,  Jonathan Lemoine ,  Kevin Zacchera

IPC: F01D9/04 ,  F01D25/28 ,  F01D9/06 ,  F01D11/00 ,  F01D25/16 ,  F01D25/12

CPC classification number: F01D25/28 ,  F01D9/042 ,  F01D9/065 ,  F01D11/003 ,  F01D25/12 ,  F01D25/162 ,  F05D2220/3213 ,  F05D2240/58 ,  F05D2260/20 ,  Y02T50/675

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. The mid-turbine frame also includes multiple spokes protruding radially outward from the inner frame case. The mid-turbine frame also includes at least one service line connected to the inner frame case.

公开(公告)号：US20160047269A1

公开(公告)日：2016-02-18

申请号：US14823568

申请日：2015-08-11

Applicant: United Technologies Corporation

Inventor： Kevin Zacchera ,  Patrick D. Couture

IPC: F01D21/00 ,  F01D11/20 ,  F01D5/22

CPC classification number: F01D21/003 ,  F01D5/225 ,  F01D11/20 ,  F05D2220/30 ,  F05D2240/11 ,  F05D2260/81 ,  F05D2260/83 ,  F05D2270/20 ,  F05D2270/44 ,  F05D2270/71

Abstract: A method is provided for calibrating an active clearance control system for a plurality of turbine engines. During this method, a squeeze test is performed between a tip of a rotor blade and a shroud. Results of the squeeze test are applied to adjust a gap between the tip and the shroud. The performance of the squeeze test and the application of the results may be individually performed for each of the turbine engines.

Abstract translation: 提供了一种用于校准多个涡轮发动机的主动间隙控制系统的方法。 在该方法中，在转子叶片的尖端和护罩之间进行挤压试验。 应用挤压试验的结果来调整尖端和护罩之间的间隙。 挤压试验的性能和结果的应用可以针对每个涡轮发动机单独执行。