公开(公告)号：US11371372B2

公开(公告)日：2022-06-28

申请号：US16776203

申请日：2020-01-29

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/06

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

公开(公告)号：US11286793B2

公开(公告)日：2022-03-29

申请号：US16545451

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 joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between. The cooling apertures of the first and second ribs open at the cooling channel such that there is a cooling circuit in which the rib passages of the first and second ribs are fluidly connected through the cooling apertures and the cooling channel.

公开(公告)号：US20210148235A1

公开(公告)日：2021-05-20

申请号：US16683640

申请日：2019-11-14

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack ,  JinQuan Xu

IPC: F01D5/18

Abstract: An airfoil include an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes a first arm by which the rib is solely connected to the first side wall, and second and third arms by which the rib is solely connected to the second side wall.

公开(公告)号：US20210140323A1

公开(公告)日：2021-05-13

申请号：US16682453

申请日：2019-11-13

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.

公开(公告)号：US10934857B2

公开(公告)日：2021-03-02

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 ,  F01D5/28

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：US10731476B2

公开(公告)日：2020-08-04

申请号：US16005755

申请日：2018-06-12

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Brandon W. Spangler

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

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section. A baffle includes an elongated body arranged in the second passage section to define a pair of cooling flow paths respectively established along a pair of opposed walls of the elongated body such that the pair of cooling flow paths extend from the turn section along a common length of the second passage section, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the pair of cooling flow paths.

公开(公告)号：US10690346B2

公开(公告)日：2020-06-23

申请号：US15476431

申请日：2017-03-31

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Atul Kohli ,  Dustin W. Davis ,  Ricardo Trindade ,  Steven Bruce Gautschi ,  Brandon W. Spangler ,  Trevor Rudy ,  Benjamin Bellows ,  Dave J. Hyland ,  James B. Hoke ,  Stephen K. Kramer ,  Dennis M. Moura

IPC: F23R3/00 ,  F23R3/60 ,  F23R3/06 ,  F16B43/00

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

公开(公告)号：US10648351B2

公开(公告)日：2020-05-12

申请号：US15832948

申请日：2017-12-06

Applicant: United Technologies Corporation

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

IPC: F01D9/02 ,  F01D9/04 ,  F02C7/141 ,  F02C3/04 ,  F01D5/18 ,  F01D5/14

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 an internal cavity that has an inlet on 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 is at least partially aligned with the inlet.

公开(公告)号：US10590785B2

公开(公告)日：2020-03-17

申请号：US14823394

申请日：2015-08-11

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D9/06

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

公开(公告)号：US20190330986A1

公开(公告)日：2019-10-31

申请号：US15961930

申请日：2018-04-25

Applicant: United Technologies Corporation

Inventor： Corey D. Anderson ,  Brandon W. Spangler

IPC: F01D5/18

Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.