公开(公告)号：US11286787B2

公开(公告)日：2022-03-29

申请号：US15266855

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Dominic J. Mongillo ,  Atul Kohli

IPC: F01D5/18 ,  F01D25/12 ,  F04D29/58 ,  F01D9/02 ,  F01D11/08 ,  F04D29/08 ,  F04D29/32 ,  F04D29/54

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.

公开(公告)号：US10677066B2

公开(公告)日：2020-06-09

申请号：US15018072

申请日：2016-02-08

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Kyle C. Lana

IPC: F01D5/06 ,  F01D5/14 ,  F02C3/04 ,  F04D29/32 ,  F04D29/68 ,  F01D5/20 ,  F01D11/08

Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.

公开(公告)号：US10577936B2

公开(公告)日：2020-03-03

申请号：US14914762

申请日：2014-08-21

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  John W. Magowan

IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/08 ,  F01D5/22 ,  F01D11/00

Abstract: Turbomachinery hardware, used in a rotor assembly and a stator assembly, including an airfoil portion including a leading edge, a trailing edge, a pressure side, and a suction side, and a platform on which the airfoil portion is disposed. The platform including a platform axis, a pressure side mateface located adjacent to the pressure side of the airfoil portion and a suction side mateface located adjacent to the suction side airfoil portion, wherein a portion of a pressure side mateface includes a first geometry, and a portion of a suction side mateface includes a second geometry. The first geometry is selected from a group consisting of: oblique to a platform axis, and a first curved portion. The second geometry is selected from a group consisting of: oblique to the platform axis and a second curved portion.

公开(公告)号：US10422230B2

公开(公告)日：2019-09-24

申请号：US15008148

申请日：2016-01-27

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Mark F. Zelesky ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F23R3/00 ,  F01D9/02 ,  F01D5/22 ,  F01D11/08 ,  F01D25/24 ,  F01D25/12 ,  F02C7/18 ,  F01D9/06

Abstract: A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.

公开(公告)号：US10323524B2

公开(公告)日：2019-06-18

申请号：US14707092

申请日：2015-05-08

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18 ,  F01D11/24

Abstract: A component for use in a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A first skin core passage is defined immediately adjacent one of the first surface and the second surface. At least 80% of coolant entering the first skin core passage is expelled from the turbine engine component at the aft edge.

公开(公告)号：US20180306038A1

公开(公告)日：2018-10-25

申请号：US16014933

申请日：2018-06-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Scott D. Lewis ,  Christopher Corcoran

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2250/183 ,  F05D2260/201

Abstract: An airfoil having one-sided pedestals is disclosed. The airfoil may define various cavities, such as an inflow feed cavity, an impingement cavity, and an outflow cavity. The various cavities may be connected by crossover sections such as an inflow crossover section and an outflow crossover section. Cooling air may be conducted into the inflow feed cavity, out of the inflow feed cavity through an inflow crossover section into an impingement cavity, and through an impingement cavity. The cooling air may be conducted out of the impingement cavity and into an outflow cavity through an outflow crossover section. Various cavities may include one-wall pedestals. One-wall pedestals may be structures extending from a wall of a cavity into the void of the cavity, whereupon cooling air may impinge, effectuating convective cooling.

公开(公告)号：US20170145848A1

公开(公告)日：2017-05-25

申请号：US14945835

申请日：2015-11-19

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D11/08 ,  F01D25/12 ,  F16J15/16

CPC classification number: F01D11/08 ,  F01D5/081 ,  F01D5/10 ,  F01D5/3007 ,  F01D11/008 ,  F01D25/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/307 ,  F05D2240/55 ,  F16J15/162 ,  Y02T50/672 ,  Y02T50/675

Abstract: A seal arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, a component including a body having a cold side surface adjacent to a mate face, and a seal member including a leading edge region and a trailing edge region spaced by sidewalls. The seal member defines one or more grooves. The one or more grooves abut the cold side surface to define one or more cooling passages, with at least one of the one or more cooling passages having a flared inlet defined by a corresponding one of the one or more grooves.

公开(公告)号：US20170145828A1

公开(公告)日：2017-05-25

申请号：US15018072

申请日：2016-02-08

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Kyle C. Lana

IPC: F01D5/14 ,  F04D29/32 ,  F04D29/68 ,  F02C3/04 ,  F01D5/06

Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a tip shelf located in a surface of the tip proximate to a pressure side of the airfoil, wherein the tip shelf has a ledge portion extending from the pressure side to a wall portion extending upwardly from the ledge portion to the tip and wherein the wall portion is configured to have a convex portion with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.

公开(公告)号：US20170089206A1

公开(公告)日：2017-03-30

申请号：US14871456

申请日：2015-09-30

Applicant: United Technologies Corporation

Inventor： San Quach ,  Steven Bruce Gautschi ,  Matthew A. Devore ,  Scott D. Lewis ,  Matthew S. Gleiner ,  Christopher King ,  Christopher Corcoran ,  David Donald Chapdelaine

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

公开(公告)号：US20160177733A1

公开(公告)日：2016-06-23

申请号：US14639507

申请日：2015-03-05

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Gaurav M. Patel ,  Jeffery Scott Hembree ,  San Quach ,  Mark F. Zelesky ,  David J. Candelori ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F01D5/28 ,  F01D11/08 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/186 ,  B23P2700/06 ,  F01D5/147 ,  F01D5/288 ,  F01D9/041 ,  F01D11/08 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/90 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/676

Abstract: A method of forming a component for use in a gas turbine engine comprises the steps of determining a desired shape for a cooling hole on a gas turbine engine component, and determining the likely deposition of a coating to be provided on the component into the cooling hole. An intermediate cooling hole is formed that has an enlarged area from the desired shape to account for deposition of the coating. The component is then coated. A component and an intermediate component for use in a gas turbine engine are also disclosed.

Abstract translation: 一种形成用于燃气涡轮发动机的部件的方法包括以下步骤：确定燃气涡轮发动机部件上的冷却孔的期望形状，以及确定要提供到部件上的涂层可能沉积到冷却孔 。 形成中间冷却孔，该中间冷却孔具有从期望形状的放大区域以解决涂层的沉积。 然后将组分涂覆。 还公开了一种用于燃气涡轮发动机的部件和中间部件。