Country
Full text data for US,EP,CN
Type
Legal Validity
Legal Status
Filing Date
Publication Date
Inventor
Assignee
Click to expand
IPC(Section)
IPC(Class)
IPC(Subclass)
IPC(Group)
IPC(Subgroup)
Agent
Agency
Claims Number
Figures Number
Citation Number of Times
Assignee Number
No. Publication Number Title Publication/Patent Number Publication/Patent Number Publication Date Publication Date
Application Number Application Number Filing Date Filing Date
Inventor Inventor Assignee Assignee IPC IPC
1
EP3453964B1
DIRT COLLECTOR SYSTEM
Publication/Patent Number: EP3453964B1 Publication Date: 2021-01-13 Application Number: 18192485.3 Filing Date: 2018-09-04 Inventor: Clum, Carey   Snyder, Timothy S.   Assignee: United Technologies Corporation   IPC: F23R3/00
2
CN112178691A
一种带气膜孔双曲扰流柱的双层壁冷却结构
Substantial Examination
Publication/Patent Number: CN112178691A Publication Date: 2021-01-05 Application Number: 202011159378.8 Filing Date: 2020-10-27 Inventor: 朱惠人   徐志鹏   郭涛   张丽   许卫疆   李鑫磊   周道恩   Assignee: 西北工业大学   IPC: F23R3/00 Abstract: 本发明一种带气膜孔双曲扰流柱的双层壁冷却结构,属于燃气涡轮发动机领域;包括气膜孔板、冲击孔板以及设置于两板之间的若干带气膜孔双曲扰流柱,形成双层壁冷却结构;冲击孔位于冲击孔板上,其轴向垂直于冲击孔板;气膜孔位于气膜孔板上,其轴向与涵道气流方向成20‑90°倾角;冲击孔和气膜孔沿气流方向呈周期性交错排列;带气膜孔双曲扰流柱为带有双曲扰流柱内气膜孔;使得冷却气流通过双曲扰流柱内气膜孔从冷气涵道一侧通入到燃气涵道一侧。相比传统结构,冷气的贴敷效果更好,沿程冷效大幅度提高。
3
CN112178693A
一种用于波纹隔热屏的偏置孔排加圆柱孔排组合冷却结构
Substantial Examination
Publication/Patent Number: CN112178693A Publication Date: 2021-01-05 Application Number: 202011159457.9 Filing Date: 2020-10-27 Inventor: 朱惠人   徐志鹏   张丽   刘存良   许卫疆   李鑫磊   郭涛   Assignee: 西北工业大学   IPC: F23R3/00 Abstract: 本发明一种用于波纹隔热屏的偏置孔排加圆柱孔排组合冷却结构,属于航空发动机燃烧室的冷却技术领域;包括波纹隔热屏板以及设置于波纹隔热屏板上的偏置气膜孔排和圆柱孔排;所述波纹隔热屏板为圆筒结构,其内为燃气通道,由圆筒形波纹隔热屏板和燃烧室外筒体组成的环形通道形成冷气通道;所述波纹隔热屏板的每个波纹都包括迎风面和背风面,所述迎风面沿圆筒形波纹隔热屏板的轴向均布有2‑3排偏置气膜孔排,所述背风面沿圆筒形波纹隔热屏板的轴向均布有3‑4排圆柱孔排;通过在波纹板主流背风面布置多排偏置气膜孔排和迎风面布置多排圆柱气膜孔排而成,该结构可用于涡扇发动机加力燃烧室或冲压发动机燃烧室。
4
CN112178692A
一种带L型冲击孔板的纵向波纹冷却结构
Substantial Examination
Publication/Patent Number: CN112178692A Publication Date: 2021-01-05 Application Number: 202011159453.0 Filing Date: 2020-10-27 Inventor: 朱惠人   徐志鹏   刘存良   张丽   许卫疆   李鑫磊   Assignee: 西北工业大学   IPC: F23R3/00 Abstract: 本发明一种带L型冲击孔板的纵向波纹冷却结构,属于航空发动机燃烧室的冷却技术领域;包括波纹气膜孔板和L型冲击孔板,所述波纹气膜孔板为圆筒波纹管结构,作为加力燃烧室内壁,其内为主燃气涵道,L型冲击孔板的两端分别焊接于波纹气膜孔板的相邻波谷上;波纹气膜孔板的波纹包括迎风面和背风面,迎风面沿轴向均布2‑3排气膜孔,背风面沿轴向均布3‑4排气膜孔;L型冲击孔板垂直于波纹气膜孔板轴向的一侧板面为扰流柱,高度为H,其平行于波纹气膜孔板轴向的板面上开有多排冲击孔。其结构可在两方面强化换热:冷气涵道的L型冲击孔板上的L型肋扰流增加换热;冷气经冲击孔通过冲击对流换热方式带走波纹气膜板的冷量,冲击换热可以形成高换热区。
5
CN110741205B
燃烧器
Grant
Publication/Patent Number: CN110741205B Publication Date: 2021-01-26 Application Number: 201780084249.7 Filing Date: 2017-11-21 Inventor: M.j.奥唐纳   Assignee: 贝克特瓦斯公司   IPC: F23R3/28 Abstract: 一种燃料燃烧器包括管,该管从第一端延伸到第二端并且具有外表面和限定中心通道的内表面。中心通道在第一端处被供应有在管的上游预混合的空气和可燃烧燃料的混合物。第二端由端壁以流体密封的方式封闭。管包括流体导引结构用于将预混合的混合物从中心通道径向向外导引到管的外部,使得预混合的混合物沿着管的外部绕中心轴线径向地旋转。
6
CN107866773B
用于断开燃气涡轮发动机中连焰管组件的工具套件及方法
Grant
Publication/Patent Number: CN107866773B Publication Date: 2021-01-19 Application Number: 201710897926.9 Filing Date: 2017-09-28 Inventor: T.j.加特梅耶   S.c.汉森   B.t.奥维拜   Assignee: 通用电气公司   IPC: B25B27/00 Abstract: 本发明涉及一种用于断开燃气涡轮发动机中连焰管组件的工具套件及方法,具体而言,公开了一种用于使伸缩管与燃气涡轮发动机的第一衬套断开的工具套件。工具套件包括联接到燃烧器壳的基板。柱从基板向外延伸到由衬套限定的燃烧室中。柱塞可滑动地安装到柱,且可在延伸位置与收缩位置之间滑动。杆臂枢转地联接到柱和柱塞。使杆臂沿第一方向枢转使柱塞滑动至延伸位置,以使伸缩管与衬套断开。保持夹联接到燃烧器壳,且延伸到至少部分地限定在衬套与燃烧器壳之间的环形气室中。保持夹限定缺口,该缺口在柱塞组件使伸缩管与衬套断开之后收纳伸缩管。
7
EP3759394A1
COMBUSTION CHAMBER HAVING A DOUBLE CHAMBER BOTTOM
Publication/Patent Number: EP3759394A1 Publication Date: 2021-01-06 Application Number: 19717522.7 Filing Date: 2019-02-28 Inventor: Bunel, Jacques Marcel Arthur   Joory, Dan Ranjiv   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F23R3/00
8
CN112178690A
一种燃烧室机匣
Substantial Examination
Publication/Patent Number: CN112178690A Publication Date: 2021-01-05 Application Number: 202010990124.4 Filing Date: 2020-09-18 Inventor: 时远   赵弦   宋宇佳   郭凯   曾宇晖   何鹏   邓远灏   李九龙   张伟   卢加平   徐兵   姜山   Assignee: 中国航发四川燃气涡轮研究院   IPC: F23R3/00 Abstract: 本发明属于航空发动机领域,尤其涉及小型弹用航空发动机领域,具体涉及一种燃烧室机匣。包括外机匣组件、内机匣组件和压气机末级静子叶片组;外机匣组件与内机匣组件通过压气机末级静子叶片组连接;内机匣组件包括压气机轴承座、涡轮轴承座和至少两组内机匣筒体;各内机匣筒体分层套装于压气机轴承座与涡轮轴承座之间,压气机轴承座上开设有进气口,涡轮轴承座上开设有出气口;各内机匣筒体之间形成进气口与出气口之间的空气通道。该种燃烧室机匣布局结构,功能集成度高,有效的利用了发动机空间,大幅缩短了发动机轴向长度、减轻了发动机重量,实现了发动机低成本与高性能。
9
EP2868971B1
Gas turbine combustor
Publication/Patent Number: EP2868971B1 Publication Date: 2021-01-06 Application Number: 14191424.2 Filing Date: 2014-11-03 Inventor: Yokota, Osami   Hidaka, Masataka   Numata, Shohei   Tatsumi, Testuma   Assignee: Mitsubishi Power, Ltd.   IPC: F23R3/00
10
CN109563997B
具有构造成形成喷射到燃气涡轮发动机的燃烧工段中的防护空气流的喷射器组件的管道装置
Grant
Publication/Patent Number: CN109563997B Publication Date: 2021-01-12 Application Number: 201680088257.4 Filing Date: 2016-08-26 Inventor: 安德鲁·j·诺思   胡安·恩里克·波蒂略毕尔巴鄂   沃尔特·雷·拉斯特   蒂莫西·a·福克斯   Assignee: 西门子股份公司   IPC: F23R3/34 Abstract: 提供了喷射器组件(12)和包括这种喷射器组件的管道装置。喷射器组件可以包括反应物导引结构和用于将空气流喷射到燃烧工段中的装置(24、25、26),该反应物导引结构布置成将反应物流(19)输送到燃烧工段中。喷射到燃烧工段中的空气流可以布置成在反应物流被允许进入燃烧工段中时对喷射到燃烧工段中的反应物流与燃烧产物横流的相互作用进行调节。
11
US10883369B2
High temperature compliant metallic elements for low contact stress ceramic support
Publication/Patent Number: US10883369B2 Publication Date: 2021-01-05 Application Number: 15/913,722 Filing Date: 2018-03-06 Inventor: Twelves, Jr. Wendell V.   Sinnamon, Kathleen E.   Kironn, Lexia   Butcher, Evan   Ott, Joe   Lynch, Matthew E.   Assignee: United Technologies Corporation   IPC: F01D5/30 Abstract: A ceramic component retention system includes a metallic component, a ceramic component, and at least one spring element arranged between the metallic component and the ceramic component. The metallic component has a first coefficient of thermal expansion, and the ceramic component has a second coefficient of thermal expansion. The at least one spring element is configured to mechanically couple the ceramic component to the metallic component.
12
CN109083689B
凹部、冷却结构、冷却组件和形成凹部的方法
Grant
Publication/Patent Number: CN109083689B Publication Date: 2021-01-12 Application Number: 201810839089.9 Filing Date: 2018-07-26 Inventor: 付经伦   操郢   Assignee: 中国科学院工程热物理研究所   IPC: F01D5/18 Abstract: 本发明提供一种用于冷却的凹部,其中,凹部内设置凸起、第一子凹部和第二子凹部,凸起设置于第一子凹部和第二子凹部之间。本发明还提供一种冷却结构、冷却组件以及在冷却通道的壁部形成凹部的方法。
13
EP3759393A1
METHOD FOR MINIMIZING THERMOACOUSTIC INSTABILITIES OF A GAS TURBINE
Publication/Patent Number: EP3759393A1 Publication Date: 2021-01-06 Application Number: 19709640.7 Filing Date: 2019-02-26 Inventor: Marwan, Norbert   Kurths, Jürgen   Unni, Vishnu R.   Ramanpillai, Indusekharan Nair Sujith   Krishnan, Abin   Assignee: Potsdam-Institut für Klimafolgenforschung E.V.   Indian Institute Of Technology Madras (IIT Madras)   IPC: F23R3/00
14
US2021003283A1
COMBUSTOR FLOATING COLLAR MOUNTING ARRANGEMENT
Publication/Patent Number: US2021003283A1 Publication Date: 2021-01-07 Application Number: 16/502,886 Filing Date: 2019-07-03 Inventor: Baranowicz, Maximilian   Lao, Si-man Amy   Morenko, Oleg   Assignee: PRATT & WHITNEY CANADA CORP.   IPC: F23R3/28 Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.
15
US10890327B2
Liner of a gas turbine engine combustor including dilution holes with airflow features
Publication/Patent Number: US10890327B2 Publication Date: 2021-01-12 Application Number: 15/896,223 Filing Date: 2018-02-14 Inventor: Gandikota, Gurunath   Nath, Hiranya Kumar   Rao, Arvind Kumar   Vise, Steven Clayton   Vukanti, Perumallu   Amble, Mayank Krisna   Cooper, Clayton Stuart   Assignee: GENERAL ELECTRIC COMPANY   IPC: F23R3/00 Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.
16
US2021003281A1
COMBUSTOR LINER FOR A GAS TURBINE ENGINE AND AN ASSOCIATED METHOD THEREOF
Publication/Patent Number: US2021003281A1 Publication Date: 2021-01-07 Application Number: 17/029,587 Filing Date: 2020-09-23 Inventor: Amble, Mayank Krisna   Vukanti, Perumallu   Vise, Steven Clayton   Benjamin, Michael Anthony   Assignee: GENERAL ELECTRIC COMPANY   IPC: F23R3/06 Abstract: A method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.
17
EP3762586A1
COMPONENT WALL OF A HOT GAS COMPONENT
Publication/Patent Number: EP3762586A1 Publication Date: 2021-01-13 Application Number: 19720433.2 Filing Date: 2019-04-12 Inventor: Geisen, Ole   Hajduk, Michael   Assignee: Siemens Aktiengesellschaft   IPC: F01D5/18
18
US10883375B2
Turboengine, and vane carrier unit for turboengine
Publication/Patent Number: US10883375B2 Publication Date: 2021-01-05 Application Number: 15/483,539 Filing Date: 2017-04-10 Inventor: Benz, Urs   Assignee: ANSALDO ENERGIA SWITZERLAND AG   IPC: F01D9/04 Abstract: A turboengine as disclosed includes an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures has a surface, the surfaces being arranged facing each other in the radial direction. At least one guide vane member includes at least one airfoil, a radially inner end and a radially outer end. The inner wall structure and the outer wall structure are jointly provided as a vane carrier unit, wherein the inner wall structure and the outer wall structure are fixedly connected to each other by at least one bridging member extending between the inner wall structure and the outer wall structure.
19
US2020141580A1
SILO COMBUSTION CHAMBER AND METHOD FOR RETROFITTING SAME
Publication/Patent Number: US2020141580A1 Publication Date: 2020-05-07 Application Number: 16/607,524 Filing Date: 2018-03-15 Inventor: Gaio, Giuseppe   Jäkel, Christian   Linnemann, Katrin   Mosquera, Ruiz Maria De La Paz   Rehmann, Sonja   Terzis, Petros   Vonnemann, Bernd   Winterstein, Michael   Assignee: Siemens Aktiengesellschaft   IPC: F23R3/00 Abstract: Provided is a silo combustion chamber comprising a vertically extending flame tube that can be lit from above and through which circulation takes place in a downward motion, the outer surface of the flame tube being provided with a plurality of cooling fluid supply openings and the inside thereof being lined with ceramic heat shield elements, the lowest heat shield elements being supported on a metal supporting ring; a conically tapered mixing tube arranged downstream from the flame tube, into which the lower region of the flame tube is set; and an outer housing that surrounds the flame tube and the mixing tube, forming an annular supply channel, the lowest heat shield elements completely covering the radially inwardly oriented surfaces of the supporting ring. Also provided is a method for retrofitting a silo combustion chamber.
20
US2020355369A1
COMBUSTOR WALL ASSEMBLY FOR GAS TURBINE ENGINE
Publication/Patent Number: US2020355369A1 Publication Date: 2020-11-12 Application Number: 16/715,022 Filing Date: 2019-12-16 Inventor: Hu, Tin-cheung John   Assignee: PRATT & WHITNEY CANADA CORP.   IPC: F23R3/00 Abstract: Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.