公开(公告)号：US10480788B2

公开(公告)日：2019-11-19

申请号：US15238443

申请日：2016-08-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  John S. Tu ,  Robert M. Sonntag ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Anthony Van

IPC: F23R3/00

Abstract: A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

公开(公告)号：US10077903B2

公开(公告)日：2018-09-18

申请号：US14886973

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

公开(公告)号：US10386067B2

公开(公告)日：2019-08-20

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/12 ,  F23R3/44 ,  F23R3/50

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

公开(公告)号：US20160195024A1

公开(公告)日：2016-07-07

申请号：US14884487

申请日：2015-10-15

Applicant: United Technologies Corporation

Inventor： James B. Hoke ,  Anthony Van

IPC: F02C9/26

CPC classification number: F02C9/263 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2260/96 ,  F05D2270/14

Abstract: Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated with the at least one aircraft engine, causing a valve coupled to a fuel supply and each of the nozzles to open when it is determined that the state of operation indicates a high power state relative to at least one threshold, and causing the valve to close when it is determined that the state of operation indicates a low power state relative to the at least one threshold.

Abstract translation: 本公开的方面旨在通过以下方式来控制燃料到与至少一个飞机发动机相关联的多个喷嘴的分配：确定与至少一个飞机发动机相关联的操作状态，导致与燃料供应连接的阀和每个 当确定操作状态相对于至少一个阈值指示高功率状态时，并且当确定操作状态指示相对于at处于低功率状态时使阀闭合 至少一个门槛。

公开(公告)号：US20180073737A1

公开(公告)日：2018-03-15

申请号：US15266036

申请日：2016-09-15

Applicant: United Technologies Corporation

Inventor： San Quach ,  Scott A. Elliott ,  Robert M. Sonntag ,  John S. Tu ,  Anthony Van ,  Joseph J. Sedor ,  Robert selinsky, JR. ,  John J. Rup, JR. ,  Neil B. Ridgeway ,  Gerard V. Cadieux ,  Jeffrey Leon ,  Monica Pacheco-Tougas ,  Lisa A. Jenkins ,  Lisa Tse ,  Andrew Cervoni ,  Frank J. Trzcinski

IPC: F23R3/00 ,  F23R3/44 ,  F02C7/12

CPC classification number: F23R3/002 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2300/611 ,  F23R3/06 ,  F23R3/44 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03045

Abstract: A wall panel assembly includes a first liner panel and a coating. The first liner panel has an inner first liner panel surface and a first liner panel outer surface each axially extending between a first liner panel first end and a first liner panel second end. The coating is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness that varies axially between the first liner panel first end and the first liner panel second end.

公开(公告)号：US20160201913A1

公开(公告)日：2016-07-14

申请号：US14886973

申请日：2015-10-19

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Monica Pacheco-Tougas ,  Timothy S. Snyder ,  Dennis M. Moura ,  Anthony Van

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.

Abstract translation: 本公开的方面涉及一种用于包含在飞行器的衬套中的冷却设计特征，包括：多个成角度的孔，以及分开任何两个成角度孔的所有组合的至少一个通孔，其中所述至少一个 通孔以基本上垂直于衬套的表面的角度定向，并且其中多个成角度孔中的每一个不平行于至少一个通孔。

公开(公告)号：US11175041B2

公开(公告)日：2021-11-16

申请号：US16598941

申请日：2019-10-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  John S. Tu ,  Robert M. Sonntag ,  Robert Selinsky, Jr. ,  John J. Rup, Jr. ,  Anthony Van

IPC: F23R3/00

Abstract: A combustor panel of a combustor may include a combustion facing surface, a cooling surface opposite the combustion facing surface, and heat transfer pins extending from the cooling surface. A grouping of the heat transfer pins may include a metallic coating.

公开(公告)号：US20160169120A1

公开(公告)日：2016-06-16

申请号：US14930743

申请日：2015-11-03

Applicant: United Technologies Corporation

Inventor： Anthony Van ,  Dennis M. Moura ,  James B. Hoke ,  Thomas A. Bush ,  Timothy J. Gaudet ,  Victor M. Pinedo ,  David Kwoka ,  Matthew G. Van Eck

IPC: F02C9/28 ,  F02C7/232 ,  F02C7/22

CPC classification number: F02C9/28 ,  F02C7/222 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2220/32 ,  F05D2270/03 ,  F05D2270/31 ,  F05D2270/331 ,  Y02T50/671

Abstract: A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations with an insufficiently filled secondary fuel line. This may be accomplished by altering a pressure in a secondary fuel line. The present disclosure allows for the elimination of individual fuel injector valves, which may reduce the total complexity and number of parts of the fuel injection system.

Abstract translation: 用于燃气涡轮发动机的燃料喷射系统可以用于确保在所有条件下成功的过渡，同时避免在不充分的二次燃料管线下的稳定状态或增加动力模式的操作的可能性。 这可以通过改变二次燃料管线中的压力来实现。 本公开允许消除单独的燃料喷射阀，这可以降低燃料喷射系统的总体复杂性和部件数量。

公开(公告)号：US09605598B2

公开(公告)日：2017-03-28

申请号：US14884487

申请日：2015-10-15

Applicant: United Technologies Corporation

Inventor： James B. Hoke ,  Anthony Van

IPC: F02C9/26 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34

CPC classification number: F02C9/263 ,  F02C7/228 ,  F02C7/232 ,  F02C9/34 ,  F05D2260/96 ,  F05D2270/14

Abstract: Aspects of the disclosure are directed to controlling a distribution of fuel to a plurality of nozzles associated with at least one aircraft engine by: determining a state of operation associated with the at least one aircraft engine, causing a valve coupled to a fuel supply and each of the nozzles to open when it is determined that the state of operation indicates a high power state relative to at least one threshold, and causing the valve to close when it is determined that the state of operation indicates a low power state relative to the at least one threshold.