公开(公告)号：US11286791B2

公开(公告)日：2022-03-29

申请号：US17030017

申请日：2020-09-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Mark C. Morris ,  David R. Waldman ,  Ardeshir Riahi

IPC: F01D5/18 ,  F01D9/06 ,  F02C7/18 ,  F23R3/00 ,  F02K1/82 ,  F01D9/02

Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion and a diffuser portion extending from the metering portion to the external surface of the body.

公开(公告)号：US11248850B2

公开(公告)日：2022-02-15

申请号：US16535608

申请日：2019-08-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Joseph Jensen ,  Jorge Alvarez ,  Francis Carbonell ,  Mark C. Morris ,  Donald G Godfrey ,  Karl Fleer

IPC: F28D1/053 ,  F02C7/10 ,  F28D21/00 ,  F28D7/16 ,  F28D9/00 ,  F28F1/02 ,  F28F1/34 ,  F28F9/26

Abstract: A heat exchanger includes a separator member that divides a first flow passage from a second flow passage. The heat exchanger also includes a plurality of first hollow members that extend across the first flow passage at respective non-orthogonal angles. The plurality of first hollow members are fluidly connected to the second flow passage. Moreover, the heat exchanger includes a plurality of second hollow members that extend across the second flow passage at respective non-orthogonal angles. The plurality of second hollow members are fluidly connected to the first flow passage.

公开(公告)号：US11156116B2

公开(公告)日：2021-10-26

申请号：US16378030

申请日：2019-04-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Benjamin Dosland Kamrath ,  Jason Smoke ,  Daniel C. Crites ,  Mark C. Morris

IPC: F01D9/04 ,  F01D11/00

Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.

公开(公告)号：US10933497B2

公开(公告)日：2021-03-02

申请号：US16059595

申请日：2018-08-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Andy Szuromi ,  Steve Starr ,  Donald G. Godfrey ,  Mark C. Morris

IPC: B23P6/04 ,  B22F3/105 ,  B22F3/15 ,  B22F3/24 ,  B22F3/26 ,  C23C10/60 ,  C22C21/00 ,  F01D5/28 ,  C23C10/28 ,  B23K15/00 ,  C23C18/16 ,  C23C18/32 ,  C23C18/38 ,  C23C18/42 ,  C25D5/48 ,  B22F5/00 ,  C22C1/04 ,  C23C26/00 ,  F01D5/00 ,  B33Y10/00 ,  B33Y99/00 ,  B22F5/04

Abstract: A method for improving the surface of an aluminum alloy article includes manufacturing the aluminum alloy article using an additive manufacturing technique, wherein the article as-manufactured includes one or more of cracks, roughness, or porosity at a surface of the article; coating the surface of the aluminum alloy article with a diffusion element, the diffusion element being capable of diffusing at least 0.2 mils into the article; heating the aluminum alloy article coated with the diffusion element to cause the diffusion element to diffuse the at least 0.2 mils into the article, thereby forming a diffusion layer of at least 0.2 mils in thickness comprising both aluminum alloy and diffusion element; and removing the diffusion layer from the aluminum alloy article, whereby upon the removing, a resulting improved surface of the article comprises fewer or smaller cracks, reduced roughness, or reduced porosity.

公开(公告)号：US20200240279A1

公开(公告)日：2020-07-30

申请号：US16260537

申请日：2019-01-29

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael Ryan Wedig ,  Jeffrey D. Harrison ,  Mark C. Morris ,  Raymond Gage

IPC: F01D9/04 ,  F01D25/12 ,  F02C7/18 ,  F02K3/06

Abstract: Disclosed is a tangential on-board injector (TOBI) system that includes an annulus and a plurality of cooling airflow passages disposed about the annulus. Each cooling airflow passage of the plurality of cooling airflow passages includes an inlet opening having a polygonal inlet cross-section, the inlet opening having an inlet cross-sectional area. Each cooling airflow passage of the plurality of cooling airflow passages further includes an outlet opening having an outlet cross-section and an outlet cross-sectional area. The inlet cross-sectional area is greater in magnitude than the outlet cross-sectional area. Also disclosed are additive manufacturing methods for manufacturing the tangential on-board injector system and gas turbine engines that incorporate the tangential on-board injector system.

公开(公告)号：US20200018190A1

公开(公告)日：2020-01-16

申请号：US16035191

申请日：2018-07-13

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel C. Crites ,  Mark C. Morris ,  Steven Whitaker ,  David Waldman

IPC: F01D25/32 ,  F01D5/20 ,  F01D5/18

Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at a positive angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle, and the at least one rib merges with at least one flow scoop to direct the particles and a portion of the cooling fluid into the inlet.

公开(公告)号：US20190383560A1

公开(公告)日：2019-12-19

申请号：US16535608

申请日：2019-08-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Joseph Jensen ,  Jorge Alvarez ,  Francis Carbonell ,  Mark C. Morris ,  Donald G. Godfrey ,  Karl Fleer

IPC: F28D1/053 ,  F28D7/16 ,  F28D9/00 ,  F28F1/34 ,  F02C7/10 ,  F28D21/00 ,  F28F1/02 ,  F28F9/26

Abstract: A heat exchanger includes a separator member that divides a first flow passage from a second flow passage. The heat exchanger also includes a plurality of first hollow members that extend across the first flow passage at respective non-orthogonal angles. The plurality of first hollow members are fluidly connected to the second flow passage. Moreover, the heat exchanger includes a plurality of second hollow members that extend across the second flow passage at respective non-orthogonal angles. The plurality of second hollow members are fluidly connected to the first flow passage.

公开(公告)号：US10252337B2

公开(公告)日：2019-04-09

申请号：US15250057

申请日：2016-08-29

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mamballykalathil Menon ,  Brian G. Baughman ,  James J. Cobb ,  Donald G. Godfrey ,  Mark C. Morris

IPC: B22F3/24 ,  B33Y10/00 ,  B33Y40/00 ,  B33Y80/00 ,  B22F3/105 ,  B22F3/15 ,  B22F5/00 ,  B22F5/04 ,  B23K15/00 ,  C22F1/10 ,  F01D5/12 ,  F01D5/14 ,  B23K101/00 ,  B23K103/08

Abstract: A method for manufacturing a metallic article includes providing or obtaining a metallic material in powder form, using an additive manufacturing process, building the metallic article from the powder-form metallic material, layer-by-layer, in a build direction, wherein as a result of the additive manufacturing process, the metallic article comprises columnar grain structures oriented in the build direction, and conveying the metallic article through a gradient furnace in a direction of conveyance from a first area of the gradient furnace to a second area of the gradient furnace to increase a size of the columnar grain structures in the metallic article. The metallic article is conveyed through the gradient furnace in an orientation such that the columnar structures oriented in the build direction are substantially parallel to the direction of conveyance.

公开(公告)号：US20180347014A1

公开(公告)日：2018-12-06

申请号：US16059565

申请日：2018-08-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Andy Szuromi ,  Hallee Zox Deutchman ,  Brian G. Baughman ,  Donald G. Godfrey ,  Harry Lester Kington ,  Mark C. Morris

IPC: C22C19/05 ,  B33Y70/00 ,  B22F3/105 ,  C22F1/10 ,  F01D5/28 ,  F01D9/02 ,  B33Y10/00

CPC classification number: C22C19/057 ,  B22F3/1055 ,  B33Y10/00 ,  B33Y70/00 ,  C22C19/05 ,  C22F1/10 ,  F01D5/28 ,  F01D9/02 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/41 ,  F05D2230/42 ,  F05D2300/175 ,  F05D2300/177

Abstract: A nickel-based superalloy component includes a nickel-based superalloy metal. The nickel-based superalloy metal includes, on a weight basis of the overall superalloy metal: about 9.5% to about 10.5% tungsten, about 9.0% to about 11.0% cobalt, about 8.0% to about 8.8% chromium, about 5.3% to about 5.7% aluminum, about 2.8% to about 3.3% tantalum, about 0.3% to about 1.6% hafnium, about 0.5% to about 0.8% molybdenum, about 0.005% to about 0.04% carbon, and a majority of nickel. In some examples, the component includes a gas turbine engine component, such as a turbine blade or a turbine vane, and the metal form of the nickel-based superalloy may be used as a filler metal for welding a casting alloy, a wrought alloy, or a powder metal alloy or other wrought forms.

公开(公告)号：US20180347013A1

公开(公告)日：2018-12-06

申请号：US16059542

申请日：2018-08-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Andy Szuromi ,  Hallee Zox Deutchman ,  Brian G. Baughman ,  Donald G. Godfrey ,  Harry Lester Kington ,  Mark C. Morris

IPC: C22C19/05 ,  B33Y70/00 ,  B22F3/105 ,  C22F1/10 ,  F01D5/28 ,  F01D9/02 ,  B33Y10/00

CPC classification number: C22C19/057 ,  B22F3/1055 ,  B33Y10/00 ,  B33Y70/00 ,  C22C19/05 ,  C22F1/10 ,  F01D5/28 ,  F01D9/02 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/41 ,  F05D2230/42 ,  F05D2300/175 ,  F05D2300/177

Abstract: A method of manufacturing a nickel-based superalloy component includes providing or obtaining, in a powdered form, a build material alloy including, on a weight basis of the overall build material alloy: about 9.5% to about 10.5% tungsten, about 9.0% to about 11.0% cobalt, about 8.0% to about 8.8% chromium, about 5.3% to about 5.7% aluminum, about 2.8% to about 3.3% tantalum, about 0.3% to about 1.6% hafnium, about 0.5% to about 0.8% molybdenum, about 0.005% to about 0.04% carbon, and a majority of nickel. The method further includes subjecting the build material alloy to a high energy density beam in an additive manufacturing process to selectively fuse portions of the build material to form a built component and subjecting the built component to a finishing process to precipitate a gamma-prime phase of the nickel-based superalloy.