公开(公告)号：US20220364727A1

公开(公告)日：2022-11-17

申请号：US17317589

申请日：2021-05-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nagaraja Rudrapatna ,  Rodolphe Dudebout

IPC: F23R3/00 ,  F02C7/18

Abstract: A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.

公开(公告)号：US20220260016A1

公开(公告)日：2022-08-18

申请号：US17178418

申请日：2021-02-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Hamdullah Ozogul ,  Atul Verma ,  Amy Kujala ,  Michael Wedig ,  Ryan Meyer ,  Bradley Culbertson

IPC: F02C7/12 ,  F23R3/00

Abstract: A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.

公开(公告)号：US11287133B2

公开(公告)日：2022-03-29

申请号：US16988119

申请日：2020-08-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Sunil James

IPC: F23R3/34 ,  F23R3/00 ,  F23R3/06 ,  F02C7/228

Abstract: A combustion system and a method of combustion for a gas turbine engine includes a combustor liner defining a combustion chamber. A plurality of fuel nozzle sets extend into, and supply fuel flow to, the combustion chamber. A pilot fuel nozzle injects a first fuel spray in a tangential direction relative to the combustion liner and toward the upstream end of the combustion chamber. A main fuel nozzle injects a second fuel spray toward the exit end of the combustion chamber. At ignition conditions, a majority of the fuel flow is injected through the pilot fuel nozzles, and at high power conditions a majority of the fuel flow is injected through the main fuel nozzles. At high power conditions, a fuel rich mixture is supplied to the combustion chamber, and a row of quench jets are configured to supply air to the combustion chamber, providing rich-quench-lean combustion.

公开(公告)号：US20210325045A1

公开(公告)日：2021-10-21

申请号：US17305202

申请日：2021-07-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Nagaraja S. Rudrapatna ,  Atul Verma ,  David Chou ,  Christopher Zollars

IPC: F23R3/04

Abstract: A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.

公开(公告)号：US10895157B2

公开(公告)日：2021-01-19

申请号：US15495663

申请日：2017-04-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Paul Yankowich

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/06 ,  F23R3/00

Abstract: A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.

公开(公告)号：US10775044B2

公开(公告)日：2020-09-15

申请号：US16172383

申请日：2018-10-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Atul Verma ,  Sunil James ,  Hamdullah Ozogul ,  John Gintert

IPC: F23R3/00

Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

公开(公告)号：US20200166211A1

公开(公告)日：2020-05-28

申请号：US16200848

申请日：2018-11-27

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Nagaraja S. Rudrapatna ,  Atul Verma ,  David Chou ,  Christopher Zollars

IPC: F23R3/04

Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.

公开(公告)号：US20200132304A1

公开(公告)日：2020-04-30

申请号：US16172383

申请日：2018-10-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Atul Verma ,  Sunil James ,  Hamdullah Ozogul ,  John Gintert

IPC: F23R3/00 ,  F02C7/18

Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.

公开(公告)号：US20180306114A1

公开(公告)日：2018-10-25

申请号：US15495663

申请日：2017-04-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rodolphe Dudebout ,  Paul Yankowich

IPC: F02C7/18 ,  F01D5/18 ,  F02C7/24 ,  F01D5/28 ,  F02C3/04

CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D5/288 ,  F02C3/04 ,  F02C7/24 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2300/611

Abstract: A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.