公开(公告)号：US10815903B2

公开(公告)日：2020-10-27

申请号：US16151596

申请日：2018-10-04

Applicant: United Technologies Corporation

Inventor： Joseph T. Caprario

IPC: F02C9/18 ,  F01D3/00 ,  F01D5/08 ,  F01D11/02 ,  F02C7/28 ,  F16J15/44 ,  F02C7/12

Abstract: A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

公开(公告)号：US10119474B2

公开(公告)日：2018-11-06

申请号：US14766192

申请日：2013-12-18

Applicant: United Technologies Corporation

Inventor： Dave J. Hyland ,  Joseph T. Caprario ,  Timothy Dale

IPC: F02C7/28 ,  F01D25/04 ,  F16J15/44 ,  F01D19/00 ,  F01D25/22 ,  F01D11/00 ,  F01D11/02

Abstract: A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea.

公开(公告)号：US20180087397A1

公开(公告)日：2018-03-29

申请号：US15274306

申请日：2016-09-23

Applicant: United Technologies Corporation

Inventor： Joseph T. Caprario ,  Noah Wadsworth ,  Mark E. Marler ,  James P. Allore ,  Elizabeth F. Vinson

IPC: F01D25/04 ,  F01D9/02

CPC classification number: F01D25/04 ,  F01D5/3015 ,  F01D5/323 ,  F01D9/02 ,  F05D2220/32 ,  F05D2260/30 ,  F05D2260/36

Abstract: A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.

公开(公告)号：US20160069269A1

公开(公告)日：2016-03-10

申请号：US14766192

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dave J. Hyland ,  Joseph T. Caprario ,  Timothy Dale

IPC: F02C7/28 ,  F16J15/44 ,  F01D25/04

CPC classification number: F02C7/28 ,  F01D11/001 ,  F01D11/025 ,  F01D19/00 ,  F01D25/04 ,  F01D25/22 ,  F05D2240/53 ,  F05D2260/85 ,  F05D2260/96 ,  F16J15/44 ,  F16J15/442

Abstract: A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea.

Abstract translation: 公开了一种适用于减少发动机冷启动时的振动的用于燃气涡轮发动机的液压密封和减振装置。 在一个公开的结构中，减振装置由具有相对高的热膨胀系数的温度敏感控制环组成，适于在较低温度下迅速膨胀以在这种燃气涡轮发动机起动期间保护静水压密封。 在操作温度下，控制环适于与静水压海相分离。

公开(公告)号：US20140178174A1

公开(公告)日：2014-06-26

申请号：US13724320

申请日：2012-12-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Joseph T. Caprario ,  Shawn J. Gregg ,  Dave J. Hyland

IPC: F01D9/02

CPC classification number: F01D9/065 ,  F05D2260/22141 ,  Y02T50/676

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.

Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括压缩机。 压缩机附近的支柱包括穿过支柱的一部分的流动通道。 流动通道构造成将空气从压缩机引导到燃气涡轮发动机的另一部分。 流动通道具有至少部分地阻碍通过流动通道的一些气流的至少一个表面特征。

公开(公告)号：US20190170067A1

公开(公告)日：2019-06-06

申请号：US16151596

申请日：2018-10-04

Applicant: United Technologies Corporation

Inventor： Joseph T. Caprario

IPC: F02C9/18 ,  F01D11/02 ,  F02C7/12 ,  F01D3/00 ,  F16J15/44 ,  F02C7/28 ,  F01D5/08

Abstract: A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

公开(公告)号：US09476313B2

公开(公告)日：2016-10-25

申请号：US13724320

申请日：2012-12-21

Applicant: United Technologies Corporation

Inventor： Joseph T. Caprario ,  Shawn J. Gregg ,  Dave J. Hyland

IPC: F01D9/02 ,  F01D9/06

CPC classification number: F01D9/065 ,  F05D2260/22141 ,  Y02T50/676

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.

Abstract translation: 根据示例性实施例，燃气涡轮发动机组件尤其包括压缩机。 压缩机附近的支柱包括穿过支柱的一部分的流动通道。 流动通道构造成将空气从压缩机引导到燃气涡轮发动机的另一部分。 流动通道具有至少部分地阻碍通过流动通道的一些气流的至少一个表面特征。

公开(公告)号：US10982565B2

公开(公告)日：2021-04-20

申请号：US14759769

申请日：2013-01-21

Applicant: United Technologies Corporation

Inventor： Dale William Petty ,  James P. Allore ,  Joseph T. Caprario ,  Steven J. Bauer

IPC: F01D25/28 ,  F01D25/24 ,  F01D25/16 ,  F01D25/26

Abstract: A turbine housing section includes a radially inner case centered on a first axis, and a radially outer case spaced radially outwardly of the inner case, and centered on a second axis. The first and second axes are offset relative to each other. A plurality of tie rods include a threaded nut received on a tie rod, with the plurality of tie rods connecting the inner and outer cases. The plurality of tie rods are spaced circumferentially about both of the first and second axes, and extend for distinct lengths between the inner and outer cases such that the inner and outer cases are held at a position wherein the first and second axes are offset.

公开(公告)号：US10215037B2

公开(公告)日：2019-02-26

申请号：US15154351

申请日：2016-05-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Joseph T. Caprario

IPC: F01D5/30 ,  F01D11/00 ,  F16B21/18

Abstract: A retaining ring assembly for a gas turbine engine may include a first engine component and a second engine component. A retaining ring may be disposed between the first engine component and the second engine component. The retaining ring may be circumferentially discontinuous and may include a first terminal portion having at least one of a tapered or a contoured geometry. A thickness of the retaining ring at the first terminal portion may be less than a thickness of the retaining ring away from the first terminal portion.

公开(公告)号：US20150226125A1

公开(公告)日：2015-08-13

申请号：US14427652

申请日：2013-03-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dale William Petty ,  Karl D. Blume ,  Joseph T. Caprario ,  Steven J. Bauer

IPC: F02C7/20 ,  F01D25/24 ,  F02C3/045

CPC classification number: F02C7/20 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F02C3/045 ,  Y02T50/671 ,  Y10T29/49826

Abstract: A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes a single-piece case structure with a turbine case portion and a transition case portion. The transition case portion is integrally formed with the turbine case portion as a single part module. A combustor case houses the combustor and an aft turbine case supports the low pressure turbine. The outer case includes a forward end attachable to the combustor case and an aft end attachable to the aft turbine.

Abstract translation: 所公开的燃气涡轮发动机包括压缩机部分，燃烧器部分，第一涡轮部分和第二涡轮部分。 用于燃气涡轮发动机的外壳结构包括具有涡轮壳体部分和过渡壳体部分的单件壳体结构。 过渡壳体部分与涡轮壳体部分整体形成为单个部件模块。 燃烧器壳体容纳燃烧器，并且后涡轮壳体支撑低压涡轮机。 外壳包括可附接到燃烧器壳体的前端和可附接到后涡轮机的后端。