公开(公告)号：US11939883B2

公开(公告)日：2024-03-26

申请号：US16532603

申请日：2019-08-06

Applicant: United Technologies Corporation

Inventor： Allan N. Arisi ,  Ricardo Trindade ,  Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F05D2260/22141

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

公开(公告)号：US11773742B2

公开(公告)日：2023-10-03

申请号：US16806168

申请日：2020-03-02

Applicant: United Technologies Corporation

Inventor： Jonathan Ortiz ,  Raymond Surace ,  Renee J. Jurek ,  Tracy A. Propheter-Hinckley

IPC: F01D11/20 ,  F02C3/04 ,  F01D5/02 ,  F02C9/18 ,  F04D29/54 ,  F01D11/24 ,  F01D9/06

CPC classification number: F01D11/20 ,  F01D5/02 ,  F01D9/065 ,  F01D11/24 ,  F02C3/04 ,  F02C9/18 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/50212 ,  Y02T50/60

Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

公开(公告)号：US11125164B2

公开(公告)日：2021-09-21

申请号：US16527422

申请日：2019-07-31

Applicant: United Technologies Corporation

Inventor： Scott A. Kovach ,  Tracy A. Propheter-Hinckley

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/04 ,  B23Q3/06

Abstract: A method of fabricating a baffle for a gas turbine engine component includes providing a baffle that has a baffle wall that circumscribes an open interior region, the baffle wall defining two datum features, wherein at least one of the two datum features is semi-spherical, establishing a fixed reference position of the baffle in a fixture by engaging the two datum features with two corresponding locators on the fixture, and performing at least one operation on the baffle that is dependent upon the reference position.

公开(公告)号：US11077494B2

公开(公告)日：2021-08-03

申请号：US15223861

申请日：2016-07-29

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  B22C9/24 ,  B22D25/02 ,  B22C9/04 ,  B22C1/00 ,  B22C9/18 ,  B22D29/00 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

公开(公告)号：US11028700B2

公开(公告)日：2021-06-08

申请号：US16594125

申请日：2019-10-07

Applicant: United Technologies Corporation

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

Abstract: An airfoil includes a cooling passage circuit that has a first plenum, a skincore passage, a first connector passage, a second plenum, and a second connector passage. The first plenum is in a first platform and extends adjacent a first side, a trailing end, and a second side of and airfoil section. The skincore passage is embedded in the first side of the airfoil section and extends longitudinally. The first connector passage is longitudinally spaced from an internal core cavity in the airfoil section so as to extend around the cavity. The first connector passage connects the first plenum with the skincore passage. The second plenum is in the second platform and extends adjacent the first side, the trailing end, and the second side of the airfoil section. The second connector passage connects the skincore passage with the second plenum.

公开(公告)号：US10987727B2

公开(公告)日：2021-04-27

申请号：US16210113

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  B22C21/14 ,  B22C7/02 ,  F01D5/14 ,  F01D5/18 ,  F01D25/14

Abstract: An investment casting core system includes first and second investment casting cores. The first investment casting core has a pin and the second investment casting core has a hole and an access slot that opens to the hole. The pin is disposed in the hole such as to space the first investment casting core in a fixed position relative to the second investment casting core. A bonding agent is disposed in the access slot and around the pin in the hole.

公开(公告)号：US20210071580A1

公开(公告)日：2021-03-11

申请号：US16594146

申请日：2019-10-07

Applicant: United Technologies Corporation

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F02C7/12 ,  F02C3/04

Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.

公开(公告)号：US20200332660A1

公开(公告)日：2020-10-22

申请号：US16594402

申请日：2019-10-07

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F01D5/18 ,  F01D5/20

Abstract: An airfoil includes an airfoil section that has an airfoil wall that define leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. The airfoil section extends form a platform. The platform defines a shelf that extends forward from the first end at the leading end of the airfoil section to a platform leading edge, aft from the first end at the trailing end of the airfoil section to a platform trailing edge, laterally from the first end at the first side of the airfoil section to a first platform side edge, and laterally from the first end at the second side of the airfoil section to a second platform side edge. The internal core cavity extends from the airfoil section into the shelf.

公开(公告)号：US10753210B2

公开(公告)日：2020-08-25

申请号：US15968865

申请日：2018-05-02

Applicant: United Technologies Corporation

Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley ,  Kyle C. Lana

IPC: F01D5/18 ,  F01D5/14

Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction, a first shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.

公开(公告)号：US10731475B2

公开(公告)日：2020-08-04

申请号：US15958056

申请日：2018-04-20

Applicant: United Technologies Corporation

Inventor： Timothy J. Jennings ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  F01D5/30

Abstract: A gas turbine engine article includes a blade that has a platform, an airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side and defines a leading end and a trailing end. The root is configured to secure the blade. The root extends radially from the non-gaspath side of the platform. The root defines forward and aft axial faces, and a radial channel in the aft axial face. The radial channel leads to an inlet orifice in the root. A cooling passage extends in the root from the inlet orifice.