公开(公告)号：US20180238240A1

公开(公告)日：2018-08-23

申请号：US15913105

申请日：2018-03-06

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Donald W. Peters ,  James P. Bangerter

IPC: F02C7/28 ,  F02C3/04 ,  F02K1/80 ,  F16J15/34

CPC classification number: F02C7/28 ,  F02C3/04 ,  F02K1/805 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/58 ,  F05D2250/14 ,  F05D2250/314 ,  F05D2250/34 ,  F05D2250/41 ,  F05D2260/38 ,  F05D2260/57 ,  F05D2300/603 ,  F05D2300/6034 ,  F16J15/3488 ,  Y02T50/672

Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.

公开(公告)号：US09880070B2

公开(公告)日：2018-01-30

申请号：US14308199

申请日：2014-06-18

Applicant: United Technologies Corporation

Inventor： David T. Feindel ,  Steven D. Porter

IPC: G01M15/14

CPC classification number: G01M15/14

Abstract: Inspection systems for a gas turbine engine (20) are provided. The inspection systems may comprise an inspection port (106), a bore-scope plug (100), a seal seat (108) and a seal (110A/110B). The bore-scope plug (100) may comprise a shaft (102A/102B) having a uniform or stepped profile. The seal (110A/110B) may be a multi-part seal (110A) or a piston seal (110B). Moreover, the bore-scope plug (100) may be configured to support, carry, and/or stabilize one or more internal structures such as, for example, a mid-turbine frame vane 82. In various embodiments, the inspection systems described herein may provide for increased inspection efficiency during development, qualification, maintenance, and event inspections.

公开(公告)号：US20170335702A1

公开(公告)日：2017-11-23

申请号：US15156993

申请日：2016-05-17

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Thomas A. Mariano

IPC: F01D11/00 ,  F01D25/04

Abstract: Aspects of the disclosure are directed to a seal comprising: a first fitting configured to couple to a first disk, and a curvic joint including curvic teeth, where a first distance between the first fitting and the curvic teeth is equal to or greater than a first thickness of the first disk. In some embodiments, an engine comprises: a compressor disk, a turbine disk, and a seal including: a first fitting configured to couple to the turbine disk, a second fitting configured to couple to the compressor disk, and a curvic joint including curvic teeth, where a first axial distance between the first fitting and the curvic teeth is greater than or equal to a first radial thickness of the turbine disk.

公开(公告)号：US09822667B2

公开(公告)日：2017-11-21

申请号：US14679305

申请日：2015-04-06

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Anthony P. Cherolis ,  Alberto A. Mateo ,  Joshua Daniel Winn ,  Seth A. Max

IPC: F01D25/00 ,  F01D25/24 ,  F16B43/00 ,  F01D9/06 ,  F01D25/16 ,  F16B39/10 ,  F01D9/02 ,  F01D9/00 ,  F16B39/24

CPC classification number: F01D25/243 ,  F01D9/00 ,  F01D9/02 ,  F01D9/065 ,  F01D25/00 ,  F01D25/162 ,  F01D25/246 ,  F16B39/101 ,  F16B39/108 ,  F16B39/24 ,  F16B43/00

Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.

公开(公告)号：US20170268351A1

公开(公告)日：2017-09-21

申请号：US15070696

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F01D9/02 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D9/02 ,  F01D5/02 ,  F01D5/066 ,  F01D5/3015 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/30 ,  F05D2260/36

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

公开(公告)号：US20160258322A1

公开(公告)日：2016-09-08

申请号：US14640323

申请日：2015-03-06

Applicant: United Technologies Corporation

Inventor： Joshua Daniel Winn ,  Anthony P. Cherolis ,  Steven D. Porter ,  Christopher Treat ,  Kevin Zacchera

IPC: F01D25/14 ,  F01D25/24

CPC classification number: F01D25/145 ,  F01D9/065 ,  F01D25/12 ,  F01D25/162 ,  F01D25/24 ,  F01D25/243 ,  F01D25/28 ,  F05D2260/20 ,  Y02T50/672 ,  Y02T50/676

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的中涡轮机框架包括第一框架壳体，联接到第一框架壳体的凸缘和邻近凸缘的相邻轮辐之间的隔热板 。 还公开了一种冷却燃气涡轮发动机的一部分的方法。

公开(公告)号：US20160215639A1

公开(公告)日：2016-07-28

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 ,  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.

Abstract translation: 根据本发明的一个实施例，密封装置包括具有内壳和每个都具有接触表面的密封环的涡轮机静态结构。 密封装置还具有带有接触表面的轴承室。 活塞密封件位于内壳体，密封环和轴承室之间，并且构造成与接触表面接触。

公开(公告)号：US20160215638A1

公开(公告)日：2016-07-28

申请号：US14603033

申请日：2015-01-22

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Seth A. Max

IPC: F01D11/00 ,  F01D25/16

CPC classification number: F01D11/005 ,  F01D11/003 ,  F01D25/12 ,  F01D25/16 ,  F02C7/08 ,  F02C7/28 ,  F05D2240/58 ,  F05D2240/581 ,  F05D2250/75 ,  F16J15/0887 ,  Y02T50/675

Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.

Abstract translation: 密封装置具有带有接触表面的涡轮机静态结构，具有接触表面的轴承室以及涡轮机静态结构和轴承室之间的空腔。 还有两个密封件，其中每个密封件构造成接触涡轮机静态结构和轴承室。

公开(公告)号：US20160169032A1

公开(公告)日：2016-06-16

申请号：US14764499

申请日：2014-01-31

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  David T. Feindel ,  Matthew Budnick ,  Conway Chuong

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80 ,  F05D2260/83 ,  G02B23/2476

Abstract: A borescope plug assembly includes a borescope plug having a shaft section and a tip section, a bushing engageable with the shaft section and a seal engageable with the tip section.

Abstract translation: 管道插头组件包括具有轴部分和尖端部分的管道插塞，可与轴部分接合的衬套和可与尖端部分接合的密封件。

公开(公告)号：US20160069200A1

公开(公告)日：2016-03-10

申请号：US14787332

申请日：2014-05-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Richard N. Allen ,  Steven D. Porter ,  Paul K. Sanchez ,  Sandra S. Pinero

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F01D9/04 ,  F01D9/047 ,  F01D25/24 ,  F05D2230/53 ,  Y02T50/671 ,  Y02T50/673

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 叶片具有在径向外平台和径向内平台之间延伸的翼型件。 至少一个平台具有标称径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称径向较薄部分的厚度。 垫片围绕在径向外平台的一侧的翼型件的外周边。 垫具有变化的径向厚度。 还公开了中涡轮机架和燃气涡轮发动机。