公开(公告)号：US10458258B2

公开(公告)日：2019-10-29

申请号：US14764021

申请日：2013-01-30

Applicant: United Technologies Corporation

Inventor： Jonathan Perry Sandoval ,  Raymond S. Hummel ,  Scott D. Virkler

IPC: F01D1/00 ,  F01D5/30 ,  F01D5/08 ,  F04D29/32 ,  F02C3/04 ,  F01D11/00 ,  F02C7/28

Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

公开(公告)号：US20190010810A1

公开(公告)日：2019-01-10

申请号：US16126482

申请日：2018-09-10

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Jaimie Schweitzer ,  Jonathan Perry Sandoval ,  Edwin Otero ,  Kyle C. Lana ,  Scott D. Virkler

IPC: F01D5/22 ,  F01D5/30 ,  F01D11/00

Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

公开(公告)号：US10907482B2

公开(公告)日：2021-02-02

申请号：US16126482

申请日：2018-09-10

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Jaimie Schweitzer ,  Jonathan Perry Sandoval ,  Edwin Otero ,  Kyle C. Lana ,  Scott D. Virkler

IPC: F01D5/30 ,  F01D5/22 ,  F01D11/00

Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

公开(公告)号：US20150369061A1

公开(公告)日：2015-12-24

申请号：US14764021

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Perry Sandoval ,  Raymond S. Hummel ,  Scott D. Virkler

IPC: F01D5/30 ,  F02C3/04

CPC classification number: F01D5/3015 ,  F01D5/082 ,  F01D11/001 ,  F02C3/04 ,  F02C7/28 ,  F04D29/321 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/676

Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

Abstract translation: 根据本公开的示例性实施例，除了其它可能的情况之外，燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器部分流体连通的涡轮机部分，处于 压缩机部分和涡轮机部分中的至少一个，至少一个与至少一个涡轮盘对应的盖板，每个盖板包括经由织带部分连接的至少两个卡扣和径向向内 所述至少两个卡扣并且经由所述织带部分连接到所述至少两个卡扣中的至少一个卡扣。

公开(公告)号：US09752447B2

公开(公告)日：2017-09-05

申请号：US14656446

申请日：2015-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Carey Clum ,  Jonathan Perry Sandoval

IPC: F23R3/06 ,  F01D5/08 ,  F01D9/02 ,  F02C7/18

CPC classification number: F01D9/023 ,  F01D5/081 ,  F02C7/18 ,  F05D2240/81 ,  F23R3/06 ,  Y02T50/672 ,  Y02T50/675

Abstract: A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various embodiments, a gas turbine engine combustor may comprise an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, and a plurality of holes in the aft combustor rail. The aft combustor rail may be positioned near an outer vane platform of a first vane stage of a turbine. Further, the plurality of holes may be designed to focus pass-through airflow onto the outer vane platform. In various embodiments, each hole of the plurality of holes may be angled between 20°-90° relative to the aft combustor rail. Additionally, the plurality of holes may be angled to converge the airflow to a focused area, such as a leading edge vane airfoil of the first vane stage.

公开(公告)号：US20150377041A1

公开(公告)日：2015-12-31

申请号：US14765491

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Julian Partyka ,  Jonathan Perry Sandoval

IPC: F01D5/32 ,  F01D11/00 ,  F01D5/12 ,  F01D5/30 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D5/32 ,  F01D5/02 ,  F01D5/082 ,  F01D5/12 ,  F01D5/3015 ,  F01D5/3046 ,  F01D11/006 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/60 ,  Y02T50/676

Abstract: In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.

Abstract translation: 根据本公开的一个方面，公开了一种转子。 转子可以包括具有中心轴的盘，从盘径向延伸的翼型，从盘径向延伸的卡口接头和锁。 锁可以进一步包括一个短突片和一个长突片，两者都从盘片径向延伸并且沿轴向相对于中心轴线方向延伸。 长突片可以具有比短突片更大的轴向长度。

公开(公告)号：US20190153939A1

公开(公告)日：2019-05-23

申请号：US16252804

申请日：2019-01-21

Applicant: United Technologies Corporation

Inventor： Jonathan Perry Sandoval

IPC: F02C3/04 ,  F01D5/06 ,  F01D5/02

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

公开(公告)号：US10221761B2

公开(公告)日：2019-03-05

申请号：US14783225

申请日：2014-04-07

Applicant: United Technologies Corporation

Inventor： Jonathan Perry Sandoval

IPC: F02C3/04 ,  F01D5/02 ,  F01D5/06

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

公开(公告)号：US09945237B2

公开(公告)日：2018-04-17

申请号：US14765491

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Julian Partyka ,  Jonathan Perry Sandoval

IPC: F01D1/00 ,  F01D5/32 ,  F01D5/08 ,  F01D5/30 ,  F01D5/02 ,  F01D5/12 ,  F01D11/00 ,  F02C3/04

CPC classification number: F01D5/32 ,  F01D5/02 ,  F01D5/082 ,  F01D5/12 ,  F01D5/3015 ,  F01D5/3046 ,  F01D11/006 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/60 ,  Y02T50/676

Abstract: In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.

公开(公告)号：US10309251B2

公开(公告)日：2019-06-04

申请号：US14770832

申请日：2014-03-10

Applicant: United Technologies Corporation

Inventor： Jonathan Perry Sandoval ,  Julian Partyka

IPC: F01D25/08 ,  F01D25/02 ,  F01D5/30 ,  F01D5/06 ,  F01D5/02

Abstract: A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with.