公开(公告)号：EP3339570B1

公开(公告)日：2020-02-19

申请号：EP17195673.3

申请日：2017-10-10

Applicant: United Technologies Corporation

Inventor： HUMMEL, Raymond S. ,  PORTER, Steven D. ,  PARTYKA, Julian

IPC: F01D5/02 ,  F01D5/30 ,  F04D29/66

公开(公告)号：EP3037627B1

公开(公告)日：2020-02-05

申请号：EP15201381.9

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  OLS, John T. ,  LANA, Kyle C.

IPC: F01D11/00 ,  F01D5/08

公开(公告)号：EP3521704A3

公开(公告)日：2019-10-16

申请号：EP19154249.7

申请日：2019-01-29

Applicant: United Technologies Corporation

Inventor： SOBANSKI, Jon E. ,  PORTER, Steven D.

IPC: F23R3/02 ,  F23R3/06

Abstract: A heat shield panel (300; 400a, 400b, 400c) for use in a gas turbine engine combustor (56) is disclosed. The heat shield panel (300; 400a, 400b, 400c) includes a hot side defining a first surface (302) having an outer perimeter, a cold side defining a second surface (304) spaced from the first surface, a rail member (308) disposed on the cold side proximate a first portion of the outer perimeter, the rail member (308) having an outer wall (310) and an inner wall (312), and an orifice (320) extending through the rail member (308), from the inner wall (312) to the outer wall (310), the orifice (320) having a cross sectional area that increases from the inner wall (312) to the outer wall (310).

公开(公告)号：EP3521704A2

公开(公告)日：2019-08-07

申请号：EP19154249.7

申请日：2019-01-29

Applicant: United Technologies Corporation

Inventor： SOBANSKI, Jon E. ,  PORTER, Steven D.

IPC: F23R3/02 ,  F23R3/06

Abstract: A heat shield panel (300; 400a, 400b, 400c) for use in a gas turbine engine combustor (56) is disclosed. The heat shield panel (300; 400a, 400b, 400c) includes a hot side defining a first surface (302) having an outer perimeter, a cold side defining a second surface (304) spaced from the first surface, a rail member (308) disposed on the cold side proximate a first portion of the outer perimeter, the rail member (308) having an outer wall (310) and an inner wall (312), and an orifice (320) extending through the rail member (308), from the inner wall (312) to the outer wall (310), the orifice (320) having a cross sectional area that increases from the inner wall (312) to the outer wall (310).

公开(公告)号：EP3048269B1

公开(公告)日：2017-12-27

申请号：EP16152299.0

申请日：2016-01-21

Applicant: United Technologies Corporation

Inventor： CHEROLIS, Anthony P. ,  FARAH, Jorge I. ,  MAX, Seth A. ,  MOSLEY, John H. ,  PORTER, Steven D. ,  REINHARDT, Gregory E. ,  ZACCHERA, Kevin

IPC: F01D25/12 ,  F01D25/16

CPC classification number: F02C7/28 ,  F01D11/005 ,  F01D25/125 ,  F01D25/162 ,  F02C3/14 ,  F02C7/06 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/55 ,  F16J15/06 ,  Y02T50/675

Abstract: A sealing arrangement 72 includes a turbine static structure with a seal ring 62 having groove 86 with a contact surface. Also included is a bearing compartment 56 with a second contact surface, and a piston seal 74 positioned between the turbine static structure and the bearing compartment 56. The piston seal 74 includes sides configured to contact the contact surfaces and is positioned in the groove 86.

公开(公告)号：EP3219909A1

公开(公告)日：2017-09-20

申请号：EP17161174.2

申请日：2017-03-15

Applicant: United Technologies Corporation

Inventor： OREN, Nicholas Waters ,  PORTER, Steven D.

IPC: F01D5/02 ,  F01D5/06 ,  F01D5/08 ,  F01D5/30

CPC classification number: F01D9/02 ,  F01D5/02 ,  F01D5/026 ,  F01D5/066 ,  F01D5/082 ,  F01D5/3015 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/30 ,  Y02T50/676

Abstract: A disc of a gas turbine engine (10) system with particular retaining ring (210; 310; 510; 610) placement and engagement implementation are provided. For example, the disc includes a disc hub (203; 403; 603) including, a groove (233; 333; 533; 633) formed on an axially extending surface (212; 312; 412; 612) of the disc hub, wherein the groove includes a forward surface (213; 313; 413; 513; 613) that extends radially into the disc hub to a groove floor (214; 314; 414; 514; 614) that is cut into the disc hub and extends axially to an aft surface (216; 316; 416; 516; 616) that extends radially outward to at least the axially extending surface of the disc hub, and a scallop (520; 521) formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web (202; 602) that extends radially outward from the disc hub, relative to an axis of rotation of the gas turbine engine.

Abstract translation: 提供了具有特定保持环（210; 310; 510; 610）放置和接合实施的燃气涡轮发动机（10）系统的盘。 例如，盘包括盘毂（203; 403; 603），盘毂包括形成在盘毂的轴向延伸表面（212; 312; 412; 612; 612）上的凹槽（233; 333; 533; 633），其中 所述凹槽包括径向延伸到所述盘毂中的前表面（213; 313; 413; 513; 613），所述前表面被切入所述盘毂并沿轴向延伸到 沿径向向外延伸至所述盘毂的所述轴向延伸表面的后表面（216; 316; 416; 516; 616）;以及沿着所述槽的至少一个表面形成的扇贝（520; 521），其中所述 扇贝构造成提供流动路径和相对于燃气涡轮发动机的旋转轴线从盘毂向外径向延伸的盘片腹板（202; 602）。

公开(公告)号：EP3048261A1

公开(公告)日：2016-07-27

申请号：EP16152189.3

申请日：2016-01-21

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D.

IPC: F01D11/00 ,  F01D25/12 ,  F16J15/08

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

Abstract: A sealing arrangement (272) of a gas turbine engine has a turbine static structure with contact surfaces on a sealing ring (262), a bearing compartment (256) with contact surfaces on a heat shield (268), and a cavity (265) between the turbine static structure and the bearing compartment. There are also two seals (74, 275), wherein each seal is configured to contact surfaces on the sealing ring of the turbine static structure and on the heat shield of the bearing compartment.

Abstract translation: 燃气涡轮发动机的密封装置（272）具有在密封环（262）上具有接触表面的涡轮机静态结构，在隔热罩（268）上具有接触表面的轴承室（256）和空腔（265） 在涡轮机静态结构和轴承室之间。 还有两个密封件（74,275），其中每个密封件构造成接触涡轮机静态结构的密封环上的表面和轴承隔室的隔热罩上。

公开(公告)号：EP3450693B1

公开(公告)日：2020-05-27

申请号：EP18191852.5

申请日：2018-08-30

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  McMAHON, Shawn M. ,  WADSWOTH, Noah ,  WHITFIELD, Christopher ,  BRADSHAW, Sean D. ,  MOURA, Dennis M. ,  ZACCHERA, Kevin

IPC: F01D9/02 ,  F01D11/00

公开(公告)号：EP3524885A1

公开(公告)日：2019-08-14

申请号：EP19155605.9

申请日：2019-02-05

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  AUXIER, James Tilsley

IPC: F23R3/00 ,  F23R3/50 ,  F23R3/60

Abstract: A heat shield panel (126, 128; 402, 404) for use in a gas turbine engine combustor (56) is disclosed. The heat shield panel (126, 128; 402, 404) includes a hot side, a cold side and at least one attachment mechanism (275; 406) having a stud (250; 408) and a central axis extending through the stud (250; 408) and a plurality of standoff pins (154; 254; 300; 410) positioned circumferentially around the stud (250; 408), the standoff pins (154; 254; 300; 410) having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.

公开(公告)号：EP3521703A1

公开(公告)日：2019-08-07

申请号：EP19154252.1

申请日：2019-01-29

Applicant: United Technologies Corporation

Inventor： PORTER, Steven D. ,  SOBANSKI, Jon E.

IPC: F23R3/00 ,  F01D5/18 ,  F01D9/06 ,  F23R3/50

Abstract: A heat shield panel (300) for a gas turbine engine combustor (56) is disclosed. The heat shield panel (300) includes a hot side defining a first surface (302) having an outer perimeter, a cold side defining a second surface (304) spaced from the first surface (302), a rail member (308) disposed on the cold side proximate a first portion of the outer perimeter, the rail member (308) having an outer wall (310) and an inner wall (312), an undercut portion (314) within the second surface (304) proximate the inner wall (310) of the rail member (308) and an orifice extending through the rail member (308), from the inner wall (310) to the outer wall (312).