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：US10316665B2

公开(公告)日：2019-06-11

申请号：US14772849

申请日：2014-03-10

Applicant: United Technologies Corporation

Inventor： Scott D. Virkler

IPC: F01D5/02 ,  F01D11/00 ,  F16J15/06 ,  F16D1/02

Abstract: A shaft coupling between a first shaft and a second shaft includes a seal assembly to minimize leakage. The seal assembly includes a ring press fit against an inner surface of the first shaft and a clearance fit with an inner surface of the second shaft. A seal is supported between the ring and the inner surface of the second shaft.

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：US20180347367A1

公开(公告)日：2018-12-06

申请号：US16001176

申请日：2018-06-06

Applicant: United Technologies Corporation

Inventor： Scott D. Virkler ,  Daniel E. Kane

IPC: F01D5/08 ,  F01D5/14 ,  F01D5/18 ,  F01D5/30

CPC classification number: F01D5/08 ,  F01D5/081 ,  F01D5/147 ,  F01D5/187 ,  F01D5/3007 ,  F01D5/3092 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2260/231 ,  F05D2260/941 ,  F05D2270/112 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk.

公开(公告)号：US10119400B2

公开(公告)日：2018-11-06

申请号：US13713257

申请日：2012-12-13

Applicant: United Technologies Corporation

Inventor： Scott D. Virkler

IPC: F01D5/02 ,  F01D5/30

Abstract: A rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live rim diameter and an outer diameter related to each other according to defined relationships.

公开(公告)号：US10107102B2

公开(公告)日：2018-10-23

申请号：US14865132

申请日：2015-09-25

Applicant: United Technologies Corporation

Inventor： Scott D. Virkler ,  Daniel E. Kane

IPC: F01D5/08 ,  F01D5/14 ,  F01D5/18 ,  F01D5/30

Abstract: A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk.

公开(公告)号：US20170292398A1

公开(公告)日：2017-10-12

申请号：US15093972

申请日：2016-04-08

Applicant: United Technologies Corporation

Inventor： David J. Wasserman ,  Scott D. Virkler ,  Eric A. Hudson ,  Ryan W. Brandt

IPC: F01D11/24 ,  F01D25/24 ,  F01D5/12

CPC classification number: F01D11/24 ,  F01D5/12 ,  F01D11/14 ,  F01D11/18 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured to allow the hot fluid to exit the thermal cavity, and at least one lifting hook configured to engage with a blade outer air seal support, wherein the thermal lifting member is configured to thermally expand outward when hot fluid is passed through the thermal cavity such that during thermal expansion the at least one lifting hook forces the blade outer air seal support to move outward.

公开(公告)号：US11280209B2

公开(公告)日：2022-03-22

申请号：US16202868

申请日：2018-11-28

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler

IPC: F01D11/02 ,  F16J15/44 ,  F01D11/00 ,  F02C7/28 ,  F01D11/16

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

公开(公告)号：US11199102B2

公开(公告)日：2021-12-14

申请号：US16202810

申请日：2018-11-28

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler

IPC: F01D11/02 ,  F01D11/00 ,  F01D11/16 ,  F16J15/44

Abstract: A hydrostatic advanced low leakage seal configured to be disposed relatively rotatable components includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a beam operatively coupling the shoe to the base, the beam having a beam length that is substantially equal to or greater than a circumferential pitch of the shoe.

公开(公告)号：US11111805B2

公开(公告)日：2021-09-07

申请号：US16202836

申请日：2018-11-28

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler

IPC: F01D11/02 ,  F01D11/00 ,  F01D11/16

Abstract: A method of manufacturing a hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components is provided. The method includes manufacturing a plurality of separate, independent components of the seal. The method also includes assembling the plurality of separate, independent components to form the seal.