公开(公告)号：US20160084502A1

公开(公告)日：2016-03-24

申请号：US14853368

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/04 ,  F02C9/16 ,  F23R3/00 ,  F02C7/04

CPC classification number: F23R3/04 ,  F01D9/02 ,  F01D9/065 ,  F02C6/06 ,  F02C7/04 ,  F02C9/16 ,  F04D29/44 ,  F05D2210/12 ,  F05D2210/13 ,  F05D2220/30 ,  F05D2240/35 ,  F23R3/005 ,  F23R3/02

Abstract: A diffuser assembly is provided for a turbine engine. This diffuser assembly includes a. diffuser module with a combustor plenum and a mixing chamber. The diffuser module is configured to receive first and second airflows into the mixing chamber and direct a mixed airflow out of the mixing chamber. The diffuser module includes a mixer configured to mix the first and the second airflows together within the mixing chamber to provide the mixed airflow.

Abstract translation: 为涡轮发动机提供扩散器组件。 该扩散器组件包括a。 扩散器模块，具有燃烧室增压室和混合室。 扩散器模块被配置为将第一和第二气流接收到混合室中并将混合气流引导出混合室。 扩散器模块包括混合器，该混合器构造成将混合室内的第一和第二气流混合在一起以提供混合气流。

公开(公告)号：US09206984B2

公开(公告)日：2015-12-08

申请号：US13630888

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： Nurhak Erbas-Sen ,  Frank J. Cunha

IPC: F23R3/00 ,  F23R3/50 ,  F23R3/16 ,  F23R3/28 ,  F23R3/04 ,  F23R3/10

Abstract: A heat shield is disclosed. The heat shield may comprise a body having a back surface and an opposite front surface, wherein an opening in the body communicates through the front and back surfaces. The heat shield may further comprise at least one radial rail disposed on the back surface and extending radially outward from the opening for directing cooling air flow.

公开(公告)号：US20150292741A1

公开(公告)日：2015-10-15

申请号：US14680649

申请日：2015-04-07

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka ,  Timothy S. Snyder

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/002 ,  F02C7/28 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00012 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A wall assembly of a combustor for a turbine engine includes a shell and a liner and a sealing interface structure. A cooling cavity is defined between the shell and liner and the sealing interface structure functions to minimize leakage out of the cooling cavity. The sealing interface structure may have a sealing width that is equal to or greater than twice the thickness of the liner and/or may include a chamber located between longitudinal segments of the sealing interface structure that inhibits leakage.

Abstract translation: 用于涡轮发动机的燃烧器的壁组件包括壳体和衬套以及密封接口结构。 在壳体和衬套之间限定了一个冷却腔，并且密封接口结构用于使冷却腔中的泄漏最小化。 密封界面结构可以具有等于或大于衬套厚度的两倍的密封宽度和/或可以包括位于密封界面结构的纵向段之间的室，其阻止泄漏。

公开(公告)号：US10670272B2

公开(公告)日：2020-06-02

申请号：US14939667

申请日：2015-11-12

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F23R3/28 ,  F23R3/10

Abstract: A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.

公开(公告)号：US10655855B2

公开(公告)日：2020-05-19

申请号：US14910964

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： James P. Bangerter ,  Kevin J. Low ,  Russell B. Hanson ,  Nurhak Erbas-Sen ,  Frank J. Cunha

IPC: F23R3/00 ,  F23R3/60 ,  F02C3/14 ,  F02C7/12 ,  F23R3/06

Abstract: A wall assembly for a combustor of a gas turbine engine is provided. The wall assembly includes a support shell with a contoured region to define at least one convergent passage between the support shell and a multiple of liner panels. A method of cooling a wall assembly for a combustor of a gas turbine engine is also provided. This method includes a step of directing cooling air into at least one convergent passage between the support shell and a multiple of liner panels.

公开(公告)号：US10344979B2

公开(公告)日：2019-07-09

申请号：US15108107

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frank J. Cunha ,  Timothy S. Snyder

IPC: F23R3/06 ,  F23R3/00 ,  F02C3/14 ,  F23M5/08 ,  F23R3/14 ,  F23R3/58

Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.

公开(公告)号：US10317078B2

公开(公告)日：2019-06-11

申请号：US15034702

申请日：2014-11-21

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka, Jr.

IPC: F23R3/10 ,  F23R3/06 ,  F23R3/00

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.

公开(公告)号：US10234140B2

公开(公告)日：2019-03-19

申请号：US15039108

申请日：2014-12-31

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Stanislav Kostka

IPC: F02C7/18 ,  F23R3/00 ,  F23R3/06 ,  F01D5/18 ,  F01D25/12

Abstract: A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.

公开(公告)号：US10222064B2

公开(公告)日：2019-03-05

申请号：US15025631

申请日：2014-09-30

Applicant: United Technologies Corporation

Inventor： Stanislav Kostka ,  Frank J. Cunha

IPC: F23R3/00 ,  F23R3/06 ,  F23M5/08 ,  F23M5/00 ,  F23R3/08 ,  F23M5/04 ,  F23R3/60

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.

公开(公告)号：US10174949B2

公开(公告)日：2019-01-08

申请号：US14765227

申请日：2014-02-05

Applicant: United Technologies Corporation

Inventor： Frank J. Cunha ,  Nurhak Erbas-Sen

IPC: F23R3/50 ,  F23R3/00 ,  F23R3/60

Abstract: A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members.