公开(公告)号：US11131212B2

公开(公告)日：2021-09-28

申请号：US15832925

申请日：2017-12-06

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Adam P. Generale ,  Ky H. Vu

IPC: F01D5/14 ,  F01D25/12 ,  F01D9/04 ,  F01D5/18

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.

公开(公告)号：US10975710B2

公开(公告)日：2021-04-13

申请号：US16210393

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic Mongillo ,  Allan N. Arisi

IPC: F01D5/18 ,  F01D9/06 ,  F01D25/12 ,  F02C7/12

Abstract: A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.

公开(公告)号：US20210054747A1

公开(公告)日：2021-02-25

申请号：US16545417

申请日：2019-08-20

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18 ,  F01D5/14

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

公开(公告)号：US10787912B2

公开(公告)日：2020-09-29

申请号：US15962074

申请日：2018-04-25

Applicant: United Technologies Corporation

Inventor： Corey D. Anderson ,  Brandon W. Spangler

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F01D9/06

Abstract: Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.

公开(公告)号：US10774657B2

公开(公告)日：2020-09-15

申请号：US16198906

申请日：2018-11-23

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo

IPC: F01D5/18

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a first platform section. The airfoil section defines an internal core cavity for conveying a fluid flow, and a baffle assembly that has a first baffle and a second baffle. The first baffle includes a first baffle body extending in the internal core cavity. The first baffle body defines an internal baffle cavity. The second baffle includes a second baffle body dimensioned to extend from the platform section into the internal baffle cavity such that an outer periphery surface of the second baffle body and an external wall of the airfoil section cooperate to define a first cooling passage that directs cooling flow into the internal baffle cavity.

公开(公告)号：US10753216B2

公开(公告)日：2020-08-25

申请号：US16105607

申请日：2018-08-20

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D9/02

Abstract: A vane includes a vane body extending from a root to an opposed tip along a longitudinal axis and first and second baffle bodies. The vane body defines a leading edge and a trailing edge, and a cavity defined between the leading edge, the trailing edge, the root and the tip. The vane body includes at least one vane rib defined between the leading edge and the trailing edge inside the cavity. The first baffle body is defined in one of a leading edge portion and a trailing edge portion of the cavity. The second baffle body is defined in a middle portion of the cavity.

公开(公告)号：US10746033B2

公开(公告)日：2020-08-18

申请号：US15982396

申请日：2018-05-17

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Jose R. Paulino

IPC: F01D9/04 ,  F01D25/12 ,  F01D5/18 ,  F01D11/00

Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.

公开(公告)号：US20200182072A1

公开(公告)日：2020-06-11

申请号：US16210146

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04

Abstract: Baffles for gas turbine engines are provided. The baffles include a baffle body extending between a first end and a second end, a chamfered surface formed at at least one corner of the baffle body, wherein the chamfered surface extends from the first end to the second end, and a plurality of baffle holes formed in the chamfered surface.

公开(公告)号：US20200182071A1

公开(公告)日：2020-06-11

申请号：US16210052

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Adam P. Generale

IPC: F01D5/18 ,  F01D5/14

Abstract: Airfoils, shells, and spars are provided. The airfoils include a shell having a first channel and a first engagement element arranged along the first channel and a spar having a second channel and a second engagement element arranged along the second channel and the spar defines an inner cavity. A connector is configured to be installed between and connect the shell and the spar to allow for thermal growth of the shell relative to the spar. The connector has first and second engageable portions connected by a link. The first engageable portion is configured to engage with the shell and the second engageable portion is configured to engage with the spar. When assembled, an outer cavity is formed between the spar and the shell, and the first and second engagement elements and the first and second engageable portions are configured to define an axial flow path through the outer cavity.

公开(公告)号：US20200182069A1

公开(公告)日：2020-06-11

申请号：US16210696

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Adam P. Generale

IPC: F01D5/18 ,  F01D9/04

Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.