公开(公告)号：US20190323360A1

公开(公告)日：2019-10-24

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.

公开(公告)号：US20190309631A1

公开(公告)日：2019-10-10

申请号：US15945170

申请日：2018-04-04

Applicant: United Technologies Corporation

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

IPC: F01D5/18

Abstract: Airfoils for gas turbine engines are provided. The airfoils include an internal cold wall defining a leading edge feed cavity proximate a leading edge and an external hot wall defining a leading edge cavity between an external wall and an internal wall. The leading edge cavity includes an inlet portion and an outlet portion. At least one impingement hole is formed in the internal wall and fluidly connects the leading edge feed cavity to the inlet portion. At least one film cooling hole is formed in the external wall and fluidly connects the outlet portion to an exterior of the airfoil body. The impingement inlet portion has a first height defined as a distance between the external wall and the internal wall for a length of the impingement inlet portion, and the film outlet portion has a second height that is greater than the first height.

公开(公告)号：US10400609B2

公开(公告)日：2019-09-03

申请号：US15866134

申请日：2018-01-09

Applicant: United Technologies Corporation

Inventor： Eric A. Hudson ,  Tracy A. Propheter-Hinckley ,  San Quach ,  Matthew A. Devore

IPC: B22C9/10 ,  B22C9/24 ,  F01D5/18

Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

公开(公告)号：US20190210929A1

公开(公告)日：2019-07-11

申请号：US15863160

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: C04B35/622 ,  F01D5/18 ,  C04B35/80 ,  C04B35/64

Abstract: A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.

公开(公告)号：US10273819B2

公开(公告)日：2019-04-30

申请号：US15246875

申请日：2016-08-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Roger Gates ,  David Richard Griffin ,  James Tilsley Auxier

IPC: F01D9/04 ,  F01D25/12 ,  F01D25/24

Abstract: A chamfered stator vane rail is provided. The chamfered stator vane rail may comprise a forward rail and an aft rail axially opposite the forward rail. The aft rail may comprise a leading edge and a trailing edge located axially opposite and aft of the leading edge. The aft rail may comprise a chamfered edge on a radially outer surface. The chamfered edge may be oriented at an angle relative to an axis.

公开(公告)号：US10252328B2

公开(公告)日：2019-04-09

申请号：US15291720

申请日：2016-10-12

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  B22C9/24 ,  B22D23/00 ,  B22D25/02 ,  F01D25/12 ,  B22C9/04 ,  F01D5/18 ,  B22C7/02 ,  F01D9/02

Abstract: A core assembly for forming a cast component includes a refractory metal core and a ceramic core element. The refractory metal core includes first and second ends and sides extending from the first end to the second end. The ceramic core element includes a slot positioned between first and second lands, each land having an inner surface facing the slot and an adjacent outer surface. The first end of the refractory metal core is secured within the slot with an adhesive, and the refractory metal core extends from the ceramic core element in both a longitudinal and a transverse direction. The slot, lands, and refractory metal core form a core assembly providing access paths to the sides of the refractory metal core. Surplus adhesive is removed from the refractory metal core via the access paths. Investment casting provides the component with an internal passage and an internal cooling circuit.

公开(公告)号：US20190101006A1

公开(公告)日：2019-04-04

申请号：US15723446

申请日：2017-10-03

Applicant: United Technologies Corporation

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

IPC: F01D5/18

Abstract: Airfoil bodies having a first core cavity and a second core cavity adjacent each other, with the second core cavity defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall. The first cavity wall is located between the second core cavity and the first core cavity and the first and second exterior walls are exterior walls of the airfoil body. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface with a first impingement flow flowing from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall and forms a first high momentum jet of impingement air thereon.

公开(公告)号：US10173264B2

公开(公告)日：2019-01-08

申请号：US14774882

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Brandon S. Donnell

IPC: B22F5/00 ,  F01D5/18 ,  B22F3/105 ,  B33Y10/00 ,  B33Y30/00 ,  F01D5/14 ,  B22F5/04 ,  F01D9/04 ,  F01D9/06 ,  B33Y80/00

Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.

公开(公告)号：US20180371941A1

公开(公告)日：2018-12-27

申请号：US15629812

申请日：2017-06-22

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Matthew A. Devore ,  Renee J. Behlman

IPC: F01D25/12 ,  F01D5/08

Abstract: A turbine engine component includes a wall extending from a leading edge to a trailing edge. The wall includes a hot side facing a gaspath when the gaspath component is in an installed state, and a cold side opposite the hot side. At least one minicore cooling circuit is disposed between the hot side and the cold side within the wall. At least one cooling fluid inlet connects the minicore cooling circuit to a coolant source. At least one film cooling hole connects the minicore cooling circuit to the hot side surface. The minicore cooling circuit includes an edge plenum having a thickness normal to the hot side surface that is larger than a thickness of the majority of the minicore cooling circuit normal to the hot side surface. The edge plenum is a portion of the at least one minicore cooling circuit most proximate to one of the leading edge and the trailing edge.

公开(公告)号：US20180283687A1

公开(公告)日：2018-10-04

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

CPC classification number: F23R3/002 ,  F16B43/00 ,  F23R3/06 ,  F23R3/60 ,  F23R2900/03044 ,  Y02T50/675

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.