公开(公告)号：US10808554B2

公开(公告)日：2020-10-20

申请号：US15354055

申请日：2016-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Michael G. McCaffrey ,  Raymond Surace ,  Matthew A. Devore

IPC: F01D5/28 ,  F01D9/06 ,  B32B18/00 ,  F01D9/04 ,  B23P15/04 ,  F01D5/18 ,  F01D25/12 ,  F04D29/38 ,  F04D29/54 ,  F01D5/14

Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

公开(公告)号：US10801333B2

公开(公告)日：2020-10-13

申请号：US15954857

申请日：2018-04-17

Applicant: United Technologies Corporation

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

IPC: B22C9/10 ,  B22C9/24 ,  B22D19/00 ,  B22D25/02 ,  F01D5/18

Abstract: Methods for manufacturing airfoils of gas turbine engines are provided. The methods include forming a main body core, the main body core including a feed cavity core portion, the main body core configured to form at least a part of an airfoil including an airfoil body, a platform, and an attachment element, forming a platform circuit core having a platform core extension, wherein the platform circuit core is configured to form a cooling circuit in the platform, wherein at least one of the feed cavity core portion and the platform core extension includes a notch, assembling the platform circuit core to the main body core such that the platform core extension engages with the feed cavity core portion at the notch, casting an airfoil using the assembled platform circuit core and main body core, and removing a platform core extension element that is formed at the location of the notch.

公开(公告)号：US10744557B2

公开(公告)日：2020-08-18

申请号：US15034612

申请日：2014-10-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dewight R. Cassells ,  Alan C. Barron ,  John P. Rizzo ,  Gordon Miller Reed ,  Tracy A. Propheter-Hinckley

IPC: B22C9/18 ,  B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54

Abstract: A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.

公开(公告)号：US10731495B2

公开(公告)日：2020-08-04

申请号：US15354243

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D11/00 ,  F01D5/12 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/08 ,  F02C3/04 ,  F01D5/00 ,  F01D5/14 ,  F04D29/28 ,  F01D5/18 ,  F04D29/58

Abstract: An airfoil includes an airfoil structure that defines a portion of an airfoil profile and a panel that defines a different portion of the airfoil profile. The panel has perimeter edges that meet the airfoil structure in a perimeter joint, and there is a perimeter seal disposed in the perimeter joint.

公开(公告)号：US10711624B2

公开(公告)日：2020-07-14

申请号：US15353896

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Matthew A. Devore ,  Adam P. Generale ,  Tracy A. Propheter-Hinckley

IPC: F01D5/28 ,  F01D9/04 ,  F01D25/08 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F02C3/04 ,  F01D5/14

Abstract: An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.

公开(公告)号：US20200180015A1

公开(公告)日：2020-06-11

申请号：US16210113

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  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：US20200149404A1

公开(公告)日：2020-05-14

申请号：US16532638

申请日：2019-08-06

Applicant: United Technologies Corporation

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

IPC: F01D5/14 ,  F01D5/18

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines 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. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.

公开(公告)号：US20200149401A1

公开(公告)日：2020-05-14

申请号：US16532617

申请日：2019-08-06

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D5/14 ,  F01D5/18

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a convex leading end, a trailing end, and first and second sides that join the convex leading end and the 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. An arced rib is disposed in the internal core cavity and arcs toward the convex leading end. The arced rib and the convex leading define there between an arced cavity. An arced baffle is disposed in the arced cavity.

公开(公告)号：US20190383147A1

公开(公告)日：2019-12-19

申请号：US16373008

申请日：2019-04-02

Applicant: United Technologies Corporation

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

IPC: F01D5/18

Abstract: A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.

公开(公告)号：US20190323361A1

公开(公告)日：2019-10-24

申请号：US15958080

申请日：2018-04-20

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F02K3/06

Abstract: A gas turbine engine article includes a blade that has a platform, and airfoil, and a root. The platform has a gaspath side and a non-gaspath side. The airfoil extends radially from the gaspath side of the platform 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 and defines forward and aft axial faces. There is an inlet orifice in the forward axial face. A cooling passage extends from the inlet orifice, through the root, and into the platform.