公开(公告)号：US20180347470A1

公开(公告)日：2018-12-06

申请号：US16108616

申请日：2018-08-22

Applicant: United Technologies Corporation

Inventor： Jeffery A. Lovett ,  Benjamin Bellows

IPC: F02C7/22 ,  F02K3/10 ,  F23R3/28 ,  F23R3/20 ,  F23R3/12 ,  F23R3/60

CPC classification number: F02C7/22 ,  F02K3/10 ,  F05D2240/36 ,  F23R3/12 ,  F23R3/20 ,  F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R3/60

Abstract: A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.

公开(公告)号：US10690346B2

公开(公告)日：2020-06-23

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 ,  F23R3/60 ,  F23R3/06 ,  F16B43/00

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.

公开(公告)号：US20160230658A1

公开(公告)日：2016-08-11

申请号：US14618572

申请日：2015-02-10

Applicant: United Technologies Corporation

Inventor： Christopher J. Hanlon ,  Daniel B. Kupratis ,  Water A. Ledwith ,  William F. Schneider ,  Sean Danby ,  Robert H. Bush ,  Benjamin Bellows

IPC: F02C7/10 ,  F02C9/18 ,  F02K3/06 ,  F02C3/34

CPC classification number: F01D25/30 ,  F01D1/023 ,  F02C7/185 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/675

Abstract: A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Abstract translation: 燃气涡轮发动机包括用于流动核心流的核心流动路径，从用于流动第二流的核心流径径向向外定位的第二流动路径，以及从第二流动路径径向向外设置用于流动辅助流的辅助流动路径。 热交换装置被构造和布置成将第二流的一部分转入辅助流路。 涡轮排气箱被构造和布置成将辅助流流动到芯流道中以与核心流混合。

公开(公告)号：US11236639B2

公开(公告)日：2022-02-01

申请号：US14618572

申请日：2015-02-10

Applicant: United Technologies Corporation

Inventor： Christopher J. Hanlon ,  Daniel B. Kupratis ,  Walter A. Ledwith ,  William F. Schneider ,  Sean Danby ,  Robert H. Bush ,  Benjamin Bellows

IPC: F01D25/30 ,  F02K3/10 ,  F02C7/18 ,  F02K3/077 ,  F02K3/075 ,  F01D1/02 ,  F02K3/02 ,  F02K3/105

Abstract: A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

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.