公开(公告)号：US10787921B2

公开(公告)日：2020-09-29

申请号：US16130126

申请日：2018-09-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Derek A Brigham ,  Jeffrey Leon ,  David Dwyer Whittle ,  Amarnath Ramlogan ,  Brian J Burke ,  Santiago Orellana ,  Tania Bhatia Kashyap ,  Dianbo Li

IPC: F01D5/30 ,  F01D11/00

Abstract: A cover plate for a rotor assembly is disclosed. In various embodiments, the cover plate includes an annular member having a radially inner portion and a radially outer portion with respect to a longitudinal axis, the radially inner portion including an aft face and an angled forward face, the angled forward face defining a forward face angle with respect to a cylindrical plane that is coaxial with the longitudinal axis, the face angle having a value that is greater than or equal to fifty degrees; a first tab and a second tab disposed proximate the radially inner portion of the annular member; and a slot disposed between the first tab and the second tab.

公开(公告)号：US20200149398A1

公开(公告)日：2020-05-14

申请号：US16592512

申请日：2019-10-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jeffrey Leon ,  WILLIAM INDOE ,  KIMBERLY CARUSO ,  BRIAN J. BURKE ,  FABIAN D. BETANCOURT ,  KURT LEACH

IPC: F01D5/02 ,  F01D5/30

Abstract: A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The bore includes a fore surface including a fore web transition portion, a fore ramp portion radially inward of the fore web transition portion and having a substantially linear portion and a fore base transition portion radially inward of the fore ramp portion. The bore also includes an aft surface including an aft web transition portion, an aft ramp portion radially inward of the aft web transition portion and having a substantially linear portion and an aft base transition portion radially inward of the aft ramp portion. A base portion of the bore includes a spool engagement surface, a first arm extending in an aft direction and a second arm extending in a fore direction and a radially extending first transition portion connecting an aft end of the spool engagement surface to a radially inward portion of the first arm and a radially extending second transition portion connecting a fore end of the spool engagement surface to a radially inward portion of the second arm.

公开(公告)号：US10550702B2

公开(公告)日：2020-02-04

申请号：US15694499

申请日：2017-09-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jeffrey Leon ,  William Indoe ,  Kimberly Caruso ,  Brian J. Burke ,  Kurt Leach ,  Fabian D. Betancourt

IPC: F01D5/30 ,  F01D5/32 ,  F01D5/02 ,  F01D11/00

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

公开(公告)号：US10386067B2

公开(公告)日：2019-08-20

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/12 ,  F23R3/44 ,  F23R3/50

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

公开(公告)号：US20180334925A1

公开(公告)日：2018-11-22

申请号：US15601271

申请日：2017-05-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas R. Hanlon ,  Jeffrey Leon

IPC: F01D25/00 ,  C23F11/00

CPC classification number: F01D25/007 ,  B05D3/02 ,  B23P9/02 ,  C21D7/08 ,  C23C24/04 ,  C23C26/00 ,  C23F11/00 ,  F01D5/005 ,  F01D5/288 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/30 ,  F05D2240/60 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/22 ,  F05D2300/611

Abstract: A repaired oxidation and corrosion resistant coating may comprise a repair material applied to a damaged portion of the oxidation and corrosion resistant coating. The repair material may be free of hexavalent chromium and may be compatible with a plurality of oxidation and corrosion resistant materials that comprise hexavalent chromium. The repair material may be burnished. The oxidation and corrosion resistant coating may comprise hexavalent chromium.

公开(公告)号：US20180163551A1

公开(公告)日：2018-06-14

申请号：US15375827

申请日：2016-12-12

Applicant: United Technologies Corporation

Inventor： John David Forbes ,  Gregory Anselmi ,  Christina E. Botnick ,  Eleanor D. Kaufman ,  Jeffrey Leon ,  Jeffrey R. Levine ,  Gerald M. Mace ,  Daniel C. Nadeau ,  Tania Bhatia Kashyap ,  Richard N. Allen

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D9/065 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2250/74 ,  F05D2260/202

Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.