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公开(公告)号：US09765968B2
公开(公告)日：2017-09-19
申请号：US13747938
申请日：2013-01-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Raymond Gage , Nagaraja S. Rudrapatna
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/50 , F23R2900/00018 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/49231
Abstract: A combustor is provided for a turbine engine. The combustor includes a first liner having a first side and a second side and a second liner having a first side and a second side. The second side of the second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber is configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second side of the first liner. The plurality of effusion cooling holes including a first effusion cooling hole extending from the first side to the second side with a non-linear line of sight.
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2.发明申请GAS TURBINE ENGINE TURBINE BLADE TIP ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD 有权气体涡轮发动机涡轮叶片提升主动间隙控制系统及方法公开(公告)号：US20150142216A1
公开(公告)日：2015-05-21
申请号：US14082755
申请日：2013-11-18
Applicant: Honeywell International Inc.
Inventor： Don Tillman , Raymond Gage , Rich Barrett
CPC classification number: B64D31/06 , F01D11/20 , F01D11/24 , F02C7/18 , F02C9/16 , F05D2260/20 , F05D2260/201 , F05D2260/57 , F05D2270/07 , F05D2270/44 , Y02T50/676
Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
Abstract translation: 在燃气涡轮发动机中控制涡轮机叶片至静止结构间隙的系统和方法包括处理飞行器数据以确定飞机何时在高度巡航条件下飞行。 当飞机在高空巡航条件下不飞行时，压缩机排放空气被引导冲击至涡轮机罩的至少一部分。 在确定飞机在高度巡航条件下飞行时，压缩机排放空气被引导流过涡轮壳体的至少一部分并且撞击到涡轮机外罩的至少一部分。
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公开(公告)号：US20140109581A1
公开(公告)日：2014-04-24
申请号：US13656219
申请日：2012-10-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Terrel Kuhn , Vinayender Kuchana , Veeraraghava Raju Hasti , Raymond Gage , Sunil James
CPC classification number: F23R3/002 , F23R3/06 , F23R3/16 , F23R3/54 , F23R2900/00015 , F23R2900/03041 , Y02T50/675
Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括环形内衬; 围绕所述环形内衬的环形外衬套; 以及燃烧器穹顶，其具有联接到所述环形内衬的第一边缘和联接到所述环形外衬垫的第二边缘，所述燃烧器圆顶形成具有所述环形内衬和所述环形外衬套的燃烧室。 燃烧室容纳通过环形内环和外环的外衬的流体流。 燃烧室在空气流的方向上会聚，以减小燃烧室的直径。 燃烧器穹顶构造成将燃烧器穹顶处的空气流分叉成指向环形内衬的第一流和指向环形外衬套的第二流。
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公开(公告)号：US09879637B2
公开(公告)日：2018-01-30
申请号：US14560521
申请日：2014-12-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mark Knowles , Shawn Alstad , Justin C. Mickelsen , Raymond Gage , Bill Russell Watson
CPC classification number: F02K3/06 , F01D25/162 , F01D25/24 , F01D25/28 , F05D2230/60 , F05D2300/121 , F05D2300/603
Abstract: A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.
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5.发明申请公开(公告)号：US20170211586A1
公开(公告)日：2017-07-27
申请号：US15006551
申请日：2016-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Raymond Gage , Bruce David Reynolds , Jeffrey D. Harrison , Michael Todd Barton , Mahmoud Mansour , Kent L. Kime
CPC classification number: F04D29/4206 , F02C3/08 , F02C6/08 , F04D29/284 , F04D29/444 , F04D29/582 , F05D2220/32 , F05D2240/128 , F05D2240/30 , F05D2260/20 , Y02T50/671
Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
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Patent Agency Ranking
6.发明申请公开(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
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.
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公开(公告)号：US10359051B2
公开(公告)日：2019-07-23
申请号：US15006551
申请日：2016-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Raymond Gage , Bruce David Reynolds , Jeffrey D. Harrison , Michael Todd Barton , Mahmoud Mansour , Kent L. Kime
Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
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8.发明申请COMBINED FAN BYPASS COMPONENTS WITH REMOVABLE FRONT FRAME STRUCTURE FOR USE IN A TURBOFAN ENGINE AND METHOD FOR MAKING SAME 有权具有可拆卸前轮架结构的风扇旁路组件，用于涡轮发动机及其制造方法公开(公告)号：US20160160800A1
公开(公告)日：2016-06-09
申请号：US14560521
申请日：2014-12-04
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mark Knowles , Shawn Alstad , Justin C. Mickelsen , Raymond Gage , Bill Russell Watson
CPC classification number: F02K3/06 , F01D25/162 , F01D25/24 , F01D25/28 , F05D2230/60 , F05D2300/121 , F05D2300/603
Abstract: A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components.
Abstract translation: 提供了一种组合风扇旁路组件并使涡轮风扇发动机中的组装接口最小化的系统和方法。 该系统和方法提供了一种减少重量的前框架结构，其可从组合的风扇旁路部件内部滑动地安装/移除。
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9.发明授权Gas turbine engine turbine blade tip active clearance control system and method 有权燃气轮机发动机叶片叶片主动间隙控制系统及方法公开(公告)号：US09266618B2
公开(公告)日：2016-02-23
申请号：US14082755
申请日：2013-11-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Tillman , Raymond Gage , Rich Barrett
CPC classification number: B64D31/06 , F01D11/20 , F01D11/24 , F02C7/18 , F02C9/16 , F05D2260/20 , F05D2260/201 , F05D2260/57 , F05D2270/07 , F05D2270/44 , Y02T50/676
Abstract: A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.
Abstract translation: 在燃气涡轮发动机中控制涡轮机叶片至静止结构间隙的系统和方法包括处理飞行器数据以确定飞机何时在高度巡航条件下飞行。 当飞机在高空巡航条件下不飞行时，压缩机排放空气被引导冲击至涡轮机罩的至少一部分。 在确定飞机在高度巡航条件下飞行时，压缩机排放空气被引导流过涡轮壳体的至少一部分并且撞击到涡轮机外罩的至少一部分。
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10.发明授权公开(公告)号：US11105212B2
公开(公告)日：2021-08-31
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
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.
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