公开(公告)号：US20160201516A1

公开(公告)日：2016-07-14

申请号：US14593779

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Steven J. Bauer ,  Jonathan Lemoine

IPC: F01D25/26 ,  F01D5/06 ,  F01D25/24

CPC classification number: F01D9/065 ,  F01D9/042 ,  F01D25/162 ,  F01D25/243 ,  F05D2220/3213 ,  F05D2230/64 ,  F05D2260/20 ,  F05D2260/31 ,  Y02T50/675

Abstract: A gas turbine engine mid-turbine frame includes an annular case which includes a first face. A tie rod includes a flange that is secured to the annular case. The flange has a perimeter that provides a second face that engages the first face and is configured to retain the flange in a generally axial direction.

Abstract translation: 燃气涡轮发动机中涡轮机架包括包括第一面的环形壳体。 拉杆包括固定到环形壳体的凸缘。 凸缘具有周边，该周边提供与第一面接合的第二面，并且构造成沿大致轴向保持凸缘。

公开(公告)号：US11118480B2

公开(公告)日：2021-09-14

申请号：US15830558

申请日：2017-12-04

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

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

公开(公告)号：US10465911B2

公开(公告)日：2019-11-05

申请号：US15156927

申请日：2016-05-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David J. Sander ,  Jonathan Lemoine

IPC: F23R3/60 ,  F02C7/20 ,  F23R3/00 ,  F01D11/00 ,  F01D25/14 ,  F01D25/24

Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.

公开(公告)号：US20190091753A1

公开(公告)日：2019-03-28

申请号：US15719357

申请日：2017-09-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael J. Schober ,  Jonathan Lemoine ,  James R. Midgley

IPC: B21D31/04 ,  B21D26/08 ,  B21D22/02 ,  B24C1/10

Abstract: A method may comprise providing an M-flange of a gas turbine engine, wherein the M-flange may comprise a bolt hole therethrough defined by a bolt hole circumference between an inner diameter and an outer diameter of the M-flange; heating a mandrel; inserting the heated mandrel into the bolt hole such that an outer edge of the heated mandrel contacts the bolt hole circumference; and plastically deforming the bolt hole circumference to strengthen the bolt hole circumference in response to the applying the heated mandrel, producing a plastically deformed bolt hole.

公开(公告)号：US20180298823A1

公开(公告)日：2018-10-18

申请号：US16011737

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Kevin Zacchera ,  Matthew Andrew Hough ,  Jonathan Lemoine ,  Christopher Treat ,  Alberto A. Mateo

IPC: F02C7/20 ,  F02C7/12 ,  F01D5/08

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

公开(公告)号：US20180292089A1

公开(公告)日：2018-10-11

申请号：US15479981

申请日：2017-04-05

Applicant: United Technologies Corporation

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

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/60 ,  F02C7/18

Abstract: A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.

公开(公告)号：US09995171B2

公开(公告)日：2018-06-12

申请号：US14598452

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Andrew D. Burdick ,  Anthony P. Cherolis ,  Christopher Treat ,  Jonathan Lemoine ,  Robert Russell Mayer ,  Jorge I. Farah ,  John H. Mosley

IPC: F01D25/12 ,  F01D5/02 ,  F01D25/26 ,  F01D5/08 ,  F01D9/06 ,  F02C7/12 ,  F01D25/16

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/081 ,  F01D9/065 ,  F01D25/125 ,  F01D25/162 ,  F01D25/26 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.

公开(公告)号：US20180087406A1

公开(公告)日：2018-03-29

申请号：US15830558

申请日：2017-12-04

Applicant: United Technologies Corporation

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

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

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. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

公开(公告)号：US20160273383A1

公开(公告)日：2016-09-22

申请号：US14663495

申请日：2015-03-20

Applicant: United Technologies Corporation

Inventor： Anthony P. Cherolis ,  Joshua Daniel Winn ,  Jonathan Lemoine

IPC: F01D25/12 ,  F01D9/06

CPC classification number: F01D25/125 ,  F01D9/065 ,  F01D25/12 ,  F01D25/162 ,  F02C7/06 ,  F02C7/18 ,  F05D2220/3213 ,  F05D2260/14 ,  F05D2260/20 ,  Y02T50/676

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.

Abstract translation: 用于燃气涡轮发动机的中涡轮机框架包括内框架壳体。 轴承支撑构件邻近内框架壳体定位。 至少一个辐条连接到内框架。 通道延伸穿过至少一个辐条，内框架壳体和轴承支撑构件。

公开(公告)号：US20160177764A1

公开(公告)日：2016-06-23

申请号：US14938447

申请日：2015-11-11

Applicant: United Technologies Corporation

Inventor： Jonathan Lemoine ,  Steven D. Porter

IPC: F01D11/00 ,  F16J15/02

CPC classification number: F01D11/005 ,  F01D9/065 ,  F01D11/003 ,  F01D25/162 ,  F02C7/28 ,  F05D2240/58 ,  F16J9/12 ,  F16J15/164 ,  F16J15/441 ,  F16J15/56

Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

Abstract translation: 可用于燃气涡轮发动机的MTF的柔性密封组件包括围绕轴线定向的壳体，壳体中沿周向延伸的凹槽径向向外敞开。 组件的环形载体被构造和布置成在凹槽内径向移动，并且包括径向向外打开的周向延伸的通道，用于接收可密封到周围圆柱形壁的活塞环。 在操作中，托架相对于壳体径向移动以补偿壳体和壁之间的径向位移，并且活塞环沿着壁轴向移动以补偿壳体和壁之间的轴向位移。