-
公开(公告)号：US08800294B2
公开(公告)日：2014-08-12
申请号：US12978954
申请日：2010-12-27
Applicant: Robert A. Ress, Jr. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
Inventor： Robert A. Ress, Jr. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
-
公开(公告)号：US09032737B2
公开(公告)日：2015-05-19
申请号：US12976517
申请日：2010-12-22
Applicant: Robert A. Ress, Jr. , Victor L. Oechsle , Randall E. Yount , Stephen A. Bergeron
Inventor： Robert A. Ress, Jr. , Victor L. Oechsle , Randall E. Yount , Stephen A. Bergeron
CPC classification number: F23R3/42 , F02K3/10 , F05D2220/80 , F23R3/06 , F23R3/26 , F23R2900/00014 , Y02T50/675
Abstract: A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.
Abstract translation: 公开了一种具有流苏的燃气涡轮发动机。 轮流器布置在燃气涡轮发动机燃烧器的下游，并且接收来自燃气涡轮发动机燃烧器的发动机排气流。 流浪者也接受旁路空气。 燃料被注入到流动者中，并且基于当地气体温度自动启动燃烧反应。 不需要使用机械火焰支架。 可以使用可滑动的阀来改变进入流浪者的旁路空气的量。 可移动的整流罩和塞子喷嘴形成燃气涡轮发动机的出口流动路径。 可移动整流罩可以被定位成基于流动者的操作来改变燃气涡轮发动机的喉部区域和出口区域，这可能受到进入流浪者的旁路空气量的影响。
-
公开(公告)号：US08938943B2
公开(公告)日：2015-01-27
申请号：US13198958
申请日：2011-08-05
Applicant: Kaare Erickson , Randall E. Yount
Inventor： Kaare Erickson , Randall E. Yount
IPC: F02K3/075
CPC classification number: F02K3/075 , F02K1/08 , F05D2270/62 , F05D2270/66
Abstract: One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Abstract translation: 本发明的一个实施例是具有旁路混合器的燃气涡轮发动机。 其他实施例包括用于燃气涡轮发动机和旁路混合器的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。
-
公开(公告)号：US08863527B2
公开(公告)日：2014-10-21
申请号：US12433104
申请日：2009-04-30
Applicant: Marcus Timothy Holcomb , Todd Taylor , Randall E. Yount
Inventor： Marcus Timothy Holcomb , Todd Taylor , Randall E. Yount
CPC classification number: F23R3/002 , F23R3/283 , F23R3/42 , Y10T29/4932
Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.
Abstract translation: 本文公开了一种用于涡轮发动机的燃烧器衬套。 燃烧器衬套包括可操作以限定涡轮发动机中的燃烧室的至少一部分的内衬面。 内衬表面沿弦弦的第一侧沿弦弦的一部分延伸。 燃烧器衬套还包括可操作以支撑浮动圆顶板的支承表面。 轴承表面的至少一部分与第二侧相对的弦弦的第二侧与弦弧间隔开。
-
Patent Agency Ranking
公开(公告)号：US20120144836A1
公开(公告)日：2012-06-14
申请号：US12978954
申请日：2010-12-27
Applicant: Robert A. Ress, JR. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
Inventor： Robert A. Ress, JR. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
IPC: F02K7/10
CPC classification number: F02C3/14 , B29L2031/08 , F01D25/30 , F02C7/20 , F02K7/10 , F05D2300/224 , F05D2300/2261 , F05D2300/2283 , F05D2300/603 , Y02T50/672
Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
Abstract translation: 本发明的一个实施例是集成的航空发动机流路结构。 另一实施例是制造集成航空发动机流路结构的方法。 其他实施例包括用于航空发动机流路结构的装置，系统，装置，硬件，方法和组合。 本申请的其他实施例，形式，特征，方面，益处和优点将从本文提供的描述和图中变得显而易见。
-
公开(公告)号：US20120067053A1
公开(公告)日：2012-03-22
申请号：US12976517
申请日：2010-12-22
Applicant: Robert A. Ress, JR. , Victor L. Oechsle , Randall E. Yount , Stephen A. Bergeron
Inventor： Robert A. Ress, JR. , Victor L. Oechsle , Randall E. Yount , Stephen A. Bergeron
CPC classification number: F23R3/42 , F02K3/10 , F05D2220/80 , F23R3/06 , F23R3/26 , F23R2900/00014 , Y02T50/675
Abstract: A gas turbine engine having a ramburner is disclosed. The ramburner is disposed downstream of a gas turbine engine combustor and receives an engine exhaust flow from the gas turbine engine combustor. The ramburner also accepts a bypass air. Fuel is injected into the ramburner and a combustion reaction is auto-initiated based upon local gas temperatures. No mechanical flame holders need be used. A slidable valve may be used to vary the amount of bypass air into the ramburner. A movable cowl and a plug nozzle form an exit flow path of the gas turbine engine. The movable cowl can be positioned to vary a throat area and exit area of the gas turbine engine based upon the operation of the ramburner, which may be influenced by the amount of bypass air entering the ramburner.
Abstract translation: 公开了一种具有流苏的燃气涡轮发动机。 轮流器布置在燃气涡轮发动机燃烧器的下游，并且接收来自燃气涡轮发动机燃烧器的发动机排气流。 流浪者也接受旁路空气。 燃料被注入到流动者中，并且基于当地气体温度自动启动燃烧反应。 不需要使用机械火焰支架。 可以使用可滑动的阀来改变进入流浪者的旁路空气的量。 可移动的整流罩和塞子喷嘴形成燃气涡轮发动机的出口流动路径。 可移动整流罩可以被定位成基于流动者的操作来改变燃气涡轮发动机的喉部区域和出口区域，这可能受到进入流浪者的旁路空气量的影响。
-
公开(公告)号：US20100275606A1
公开(公告)日：2010-11-04
申请号：US12433104
申请日：2009-04-30
Applicant: MARCUS TIMOTHY HOLCOMB , Todd Taylor , Randall E. Yount
Inventor： MARCUS TIMOTHY HOLCOMB , Todd Taylor , Randall E. Yount
CPC classification number: F23R3/002 , F23R3/283 , F23R3/42 , Y10T29/4932
Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.
Abstract translation: 本文公开了一种用于涡轮发动机的燃烧器衬套。 燃烧器衬套包括可操作以限定涡轮发动机中的燃烧室的至少一部分的内衬面。 内衬表面沿弦弦的第一侧沿弦弦的一部分延伸。 燃烧器衬套还包括可操作以支撑浮动圆顶板的支承表面。 轴承表面的至少一部分与第二侧相对的弦弦的第二侧与弦弧间隔开。
-
公开(公告)号：US08850823B2
公开(公告)日：2014-10-07
申请号：US12978954
申请日：2010-12-27
Applicant: Robert A. Ress, Jr. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
Inventor： Robert A. Ress, Jr. , Randall E. Yount , Thomas D. Destefano , Jitendra R. Patel
CPC classification number: F02C3/14 , B29L2031/08 , F01D25/30 , F02C7/20 , F02K7/10 , F05D2300/224 , F05D2300/2261 , F05D2300/2283 , F05D2300/603 , Y02T50/672
Abstract: One embodiment of the present invention is an integrated aero-engine flowpath structure. Another embodiment is a method of manufacturing integrated aero-engine flowpath structure. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aero-engine flowpath structures. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
Abstract translation: 本发明的一个实施例是集成的航空发动机流路结构。 另一实施例是制造集成航空发动机流路结构的方法。 其他实施例包括用于航空发动机流路结构的装置，系统，装置，硬件，方法和组合。 本申请的其他实施例，形式，特征，方面，益处和优点将从本文提供的描述和图中变得显而易见。
-
公开(公告)号：US20120279198A1
公开(公告)日：2012-11-08
申请号：US13198958
申请日：2011-08-05
Applicant: Kaare Erickson , Randall E. Yount
Inventor： Kaare Erickson , Randall E. Yount
CPC classification number: F02K3/075 , F02K1/08 , F05D2270/62 , F05D2270/66
Abstract: One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
Abstract translation: 本发明的一个实施例是具有旁路混合器的燃气涡轮发动机。 其他实施例包括用于燃气涡轮发动机和旁路混合器的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.014 seconds)
