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公开(公告)号：US20210131299A1
公开(公告)日：2021-05-06
申请号：US16671288
申请日：2019-11-01
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Carson A. Roy Thill
Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and mounted in a carrier. At least two of the plurality of segments have a first wall that extends radially outward from a base portion. The base portion has a radially inner side and a radially outer side. A heat shield abuts the radially outer side of the at least two segments. The heat shield is formed from a ceramic material.
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公开(公告)号：US20200248574A1
公开(公告)日：2020-08-06
申请号：US16267955
申请日：2019-02-05
Applicant: United Technologies Corporation
Inventor： Angela C. Reisch , Carson A. Roy Thill , Dairus Deylan McDowell , Jin Hu , Jeremy Drake , Gregory A. O'Connor , David M. Pons , Katelyn Kwoka
Abstract: An on-board injector for delivering discharge air toward a turbine rotor of a gas turbine engine. The on-board injector having: a first wall; a second wall spaced from said first wall to define an annular inlet and an annular exit, wherein the first wall has a first length and the second wall has a second length; and a plurality of airfoils extending between the first wall and the second wall to segregate discharge air from the annular inlet, wherein each of the plurality of airfoils extend from the annular inlet and the annular exit and completely across the first length and the second length.
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公开(公告)号：US10731493B2
公开(公告)日：2020-08-04
申请号：US14783048
申请日：2014-04-10
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Mark J. Rogers , Mark Broomer , Craig R. McGarrah , Carson A. Roy Thill
Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.
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公开(公告)号：US20160061047A1
公开(公告)日：2016-03-03
申请号：US14783048
申请日：2014-04-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M. Davis , Mark J. Rogers , Mark Broomer , Craig R. McGarrah , Carson A. Roy Thill
Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.
Abstract translation: 用于将燃气涡轮发动机定子的径向外部部件密封到其径向内部部件的密封件包括轴向弹性的密封载体，其适于安装密封载体并且在其径向内部包括一对径向间隔开的轴向延伸的， 径向弹性夹爪，其适于将密封元件（例如其间的绳索密封件）与发动机定子的径向内部部件密封接合。
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公开(公告)号：US11466585B2
公开(公告)日：2022-10-11
申请号：US16675843
申请日：2019-11-06
Applicant: United Technologies Corporation
Inventor： Jaime A. Arbona , Carson A. Roy Thill , Robin H. Fernandez , Danielle Mahoney , Andrew D. Keene , Justin K. Bleil
IPC: F01D11/08
Abstract: A flow path component assembly includes a flow path component having a plurality of segments that extend circumferentially about an axis and mounted in a support structure. At least one of the plurality of segments have a first wall and a second wall that extend radially outward from a base portion. The first wall is axially spaced from the second wall. A coating is on a portion of the first wall and a portion of the second wall. The coating is in contact with a feature on the support structure.
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Patent Agency Ranking
公开(公告)号：US11174795B2
公开(公告)日：2021-11-16
申请号：US16695616
申请日：2019-11-26
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Carson A. Roy Thill
IPC: F02C7/28
Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.
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公开(公告)号：US20210285334A1
公开(公告)日：2021-09-16
申请号：US16817990
申请日：2020-03-13
Applicant: United Technologies Corporation
Inventor： Jaime A. Arbona , Carson A. Roy Thill , Justin K. Bleil
Abstract: A component assembly includes a first component that has a first hole. The first hole has a non-circular cross section. A first portion of the first hole has a first radius of curvature and a second component. A pin extends from the second component and through the first hole. The pin has a non-circular cross section. A second portion of the pin has a second radius of curvature. The first radius of curvature and the second radius of curvature are substantially the same.
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公开(公告)号：US11105215B2
公开(公告)日：2021-08-31
申请号：US16675924
申请日：2019-11-06
Applicant: United Technologies Corporation
Inventor： Carson A. Roy Thill , Jaime A. Arbona , Justin K. Bleil , Danielle Mahoney , Andrew D. Keene
IPC: F01D11/08
Abstract: A flow path component includes a base portion that extends between a first circumferential side and a second circumferential side. A first wall and a second wall extend radially outward from the base portion. The first wall is axially spaced from the second wall to form a passage between the first and second walls. A slot is formed in the first circumferential side. A notch in the base portion extends in a radial direction from the passage to the slot.
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公开(公告)号：US20210156311A1
公开(公告)日：2021-05-27
申请号：US16695616
申请日：2019-11-26
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Carson A. Roy Thill
IPC: F02C7/28
Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.
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公开(公告)号：US20200232390A1
公开(公告)日：2020-07-23
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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