-
公开(公告)号：US10815794B2
公开(公告)日：2020-10-27
申请号：US16210146
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
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：US20200182068A1
公开(公告)日：2020-06-11
申请号：US16210606
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Adam P. Generale
Abstract: A component for a gas turbine engine. The component includes a first multiple of axial standoff ribs that extend from the first sidewall and a second multiple of axial standoff ribs that extend from the second sidewall. The structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs.
-
公开(公告)号：US20200165921A1
公开(公告)日：2020-05-28
申请号：US16198906
申请日：2018-11-23
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo
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：US10519781B2
公开(公告)日：2019-12-31
申请号：US15404252
申请日：2017-01-12
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: Airfoils having hollow bodies defining first and second airfoil cavities and having inner and outer diameter ends, a first airfoil platform at one end of the hollow body having a gaspath surface and a non-gaspath surface, wherein the hollow body extends from the gaspath surface. A first cavity opening is formed in the non-gaspath surface of the platform to fluidly connect to the first airfoil cavity and a second cavity opening in the platform is fluidly connected to the second airfoil cavity. A first turn cap is fixedly attached to the first airfoil platform on the non-gaspath surface covering the first and second cavity openings of the first airfoil platform and defines a first turning cavity such that the first cavity opening in the first airfoil platform is fluidly connected to the second cavity opening in the first airfoil platform by the first turning cavity.
-
公开(公告)号：US10465528B2
公开(公告)日：2019-11-05
申请号：US15426082
申请日：2017-02-07
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, Jr.
Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.
-
Patent Agency Ranking
公开(公告)号：US10458252B2
公开(公告)日：2019-10-29
申请号：US14955167
申请日：2015-12-01
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: A gas path component for a gas turbine engine includes an element configured to be exposed to a gas path. The element includes a plurality of internal cooling passages. At least one of the internal cooling passages includes a cross section having a plurality of asymmetrical filleted corners.
-
公开(公告)号：US20190301286A1
公开(公告)日：2019-10-03
申请号：US15938062
申请日：2018-03-28
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Corey D. Anderson
Abstract: Airfoils for gas turbine engines are provided. The airfoil include an airfoil body, the body extending between a leading edge and a trailing edge in an axial direction and between a pressure side wall and a suction side wall in a circumferential direction, the airfoil body defining an airfoil cavity therein and a baffle located within the airfoil cavity. The airfoil includes increased thickness side walls to form an airfoil cavity to account for the baffle within the cavity and to direct cooling flow through the airfoil.
-
公开(公告)号：US20190242270A1
公开(公告)日：2019-08-08
申请号：US15888237
申请日：2018-02-05
Applicant: United Technologies Corporation
Inventor： Corey D. Anderson , Brandon W. Spangler
CPC classification number: F01D11/001 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/2214 , F05D2260/22141
Abstract: Components for gas turbine engines are provided. The components include a component body having a hot side and a cold side, an attachment element extending from the cold side of the component body, a component extension extending from the component body at the attachment element to an end surface, the component extension having a cold-side first portion and a cold-side second portion, wherein the cold-side first portion is a portion of the component extension between the attachment element and the cold-side second portion, and the cold-side second portion is a portion of the component extension extending from the cold-side first portion to the end surface of the component extension, and a cold-side heat transfer augmentation feature on the cold-side second portion of the component extension, wherein the cold-side first portion defines a uniform surface.
-
公开(公告)号：US20190226345A1
公开(公告)日：2019-07-25
申请号：US16371239
申请日：2019-04-01
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, JR.
Abstract: A gas turbine engine component with a core includes a first core portion configured to provide a first cooling passage. A second core portion is spaced from the first core portion and configured to provide a second cooling passage. The second core portion includes a longitudinal leg and a resupply leg transverse to and intersecting the longitudinal leg. The resupply leg has a terminal end and is configured to provide a resupply channel A connector interconnects the terminal end to the first core portion. The connector is configured to provide a resupply hole.
-
公开(公告)号：US10309239B2
公开(公告)日：2019-06-04
申请号：US14766496
申请日：2014-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Dominic Mongillo
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.
-
-
-
-
-
-
-
-
-
Search Results
194
records
(took 0.024 seconds)
