-
公开(公告)号：US10197069B2
公开(公告)日：2019-02-05
申请号：US14947494
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Mark J. Rogers , Philip Robert Rioux
Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.
-
公开(公告)号：US10184354B2
公开(公告)日：2019-01-22
申请号：US14787320
申请日：2014-05-30
Applicant: United Technologies Corporation
Inventor： Philip Robert Rioux , Nicholas R. Leslie , Neil L. Tatman
Abstract: A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed.
-
公开(公告)号：US20170306784A1
公开(公告)日：2017-10-26
申请号：US15444971
申请日：2017-02-28
Applicant: UNITED TECHNOLOGIES CORPORATION , MTU AERO ENGINES AG
Inventor： Nicholas R. Leslie , Fadi S. Maalouf , Georg Zotz , Werner Humhauser
IPC: F01D11/12
CPC classification number: F01D11/122 , F01D11/125 , F01D11/127 , F05D2230/312 , Y02T50/6765
Abstract: A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.
-
公开(公告)号：US20170146024A1
公开(公告)日：2017-05-25
申请号：US14947494
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Mark J. Rogers , Philip Robert Rioux
CPC classification number: F04D29/526 , F01D11/08 , F01D11/12 , F01D11/122 , F01D11/18 , F01D11/24 , F04D29/164 , F04D29/321 , F05D2220/32
Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.
-
15.发明申请公开(公告)号：US20160123187A1
公开(公告)日：2016-05-05
申请号：US14893801
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas R. Leslie , Neil L. Tatman
CPC classification number: F01D25/145 , F01D11/08 , F01D25/08 , F01D25/26 , F05D2220/32 , F05D2240/15 , F05D2260/231 , Y02T50/675
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.
Abstract translation: 用于燃气涡轮发动机的隔热罩组件包括围绕轴线限定的第一隔热板段和围绕该轴限定的第二隔热板段。 在第一隔热片段和第二隔热片段之间限定双周向搭接接头。
-
Patent Agency Ranking
公开(公告)号：US10317315B2
公开(公告)日：2019-06-11
申请号：US15412572
申请日：2017-01-23
Applicant: United Technologies Corporation
Inventor： Eli Cole Warren , Nicholas R. Leslie
Abstract: A probe assembly for a gas turbine engine is disclosed. The probe assembly may include a probe, and a fastener to retain the probe within a case of the gas turbine engine, the fastener including a sealing arrangement with a heat shield of the gas turbine engine.
-
公开(公告)号：US10100670B2
公开(公告)日：2018-10-16
申请号：US14893801
申请日：2014-06-12
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Neil L. Tatman
Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.
-
公开(公告)号：US09845702B2
公开(公告)日：2017-12-19
申请号：US14697242
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , David P. Dube , Randall J. Butcher
CPC classification number: F01D25/06 , F01D25/04 , F01D25/246 , F04D29/522 , F04D29/644 , F04D29/668 , Y02T50/672
Abstract: A stator damper is disclosed. The stator damper has a body section and a damper finger. The body section rests against a stator assembly and a portion of each damper finger rests against a compressor casing. The stator damper is radially compressed between the stator assembly and the compressor casing. Thus, the stator damper exerts a radial force against the stator assembly. In this manner, relative motion of the stator assembly is damped.
-
公开(公告)号：US20170175559A1
公开(公告)日：2017-06-22
申请号：US14972893
申请日：2015-12-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Philip Robert Rioux , Nicholas R. Leslie , Richard K. Hayford
IPC: F01D11/12
CPC classification number: F01D11/12 , F01D11/122 , F01D25/246 , F04D29/526 , F05D2220/32 , F05D2230/237 , F05D2230/312 , F05D2240/11 , F05D2240/30 , F05D2250/15 , Y02T50/671
Abstract: A blade outer air seal according to an example of the present disclosure includes a seal body extending circumferentially about an axis and including at least one channel having a substantially solid radially outer surface. A substrate is radially inward of the at least one channel with respect to the axis. The substrate and the at least one channel form at least one cavity. A rotor rub strip is radially inward of the substrate.
-
公开(公告)号：US09551632B2
公开(公告)日：2017-01-24
申请号：US14107771
申请日：2013-12-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eli Cole Warren , Nicholas R. Leslie
CPC classification number: G01M15/14 , F01D11/20 , F01D17/02 , F01D21/003 , F01D25/24 , F01D25/285 , F05D2220/32 , Y10T29/4932 , Y10T403/3993
Abstract: A probe assembly for a gas turbine engine is disclosed. The probe assembly may include a probe, and a fastener to retain the probe within a case of the gas turbine engine, the fastener including a sealing arrangement with a heat shield of the gas turbine engine.
Abstract translation: 公开了一种用于燃气涡轮发动机的探针组件。 探针组件可以包括探针和将探针保持在燃气涡轮发动机的壳体内的紧固件，该紧固件包括具有燃气涡轮发动机的隔热罩的密封装置。
-
-
-
-
-
-
-
-
-
Search Results
22
records
(took 0.04 seconds)
