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1. 发明申请

WO1996008679A1 HYBRID COMBUSTOR 审中-公开
标题翻译：混合燃烧器
公开(公告)号：WO1996008679A1
公开(公告)日：1996-03-21
申请号：PCT/US1995011583
申请日：1995-09-13
申请人： ALLIEDSIGNAL INC.
发明人： ALLIEDSIGNAL INC. , HADDER, James, L.
IPC分类号： F23R03/00
CPC分类号： F23R3/46 , F23R3/007 , F23R2900/03041
摘要： A hybrid combustor (10) of a gas turbine engine includes a plurality of circularly arrayed ceramic can combustors (12) whose outlets communicate with the inlet of an annular, metal combustor (16). The combustion process is continuous through the plurality of can combustors (12) and into the single annular combustor (16). Preferably only fuel-rich combustion occurs within each of the can combustors (12), and fuel-lean combustion continues within the single annular combustor (16).
摘要翻译：燃气涡轮发动机的混合燃烧器（10）包括多个圆形排列的陶瓷罐燃烧器（12），其出口与环形金属燃烧器（16）的入口连通。燃烧过程通过多个罐式燃烧器（12）连续并进入单个环形燃烧器（16）。优选地，在每个罐式燃烧器（12）内仅发生燃料丰富的燃烧，并且在单个环形燃烧器（16）内继续燃料贫燃燃烧。

2. 发明申请

WO1992001891A1 FLAME TUBE WITH A COOLED SUPPORTING FRAME FOR A HEAT-RESISTANT LINING 审中-公开
标题翻译：具有冷却支撑框架的火焰管用于耐热衬里
公开(公告)号：WO1992001891A1
公开(公告)日：1992-02-06
申请号：PCT/DE1990000542
申请日：1990-07-17
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SIEMENS AKTIENGESELLSCHAFT
IPC分类号： F23R03/00
CPC分类号： F23R3/60 , F02K1/822 , F23M5/04 , F23R3/007 , Y02T50/675
摘要： The invention concerns a tube (1) with an interior (2) through which a stream (3) of hot gas passes. The tube has a heat shield (4) comprising a multiplicity of bricks (5) and which faces towards the interior (2) and is supported by at least one frame (6). The frame (6) is made of metal, has a multiplicity of cooling-gas feed channels (7) and a lip (9) which surrounds the tube (1) and substantially covers the channels (7) from the interior (2), leaving a slit (8). The invention calls for the support frame (6) to be securely screened from the hot gas by virtue of the fact that cooling gas fed through the channels (7) and the slit (8) forms a surface film over the frame (6), without the hot-gas stream being affected in any way. The tube (1) is particularly suited for use as a flame tube in combustion units, e.g. gas-turbine combustion chambers.
摘要翻译：本发明涉及具有内部（2）的管（1），热气流（3）通过该管。管具有包括多个砖（5）并面向内部（2）并由至少一个框架（6）支撑的隔热罩（4）。框架（6）由金属制成，具有多个冷却气体供给通道（7）和围绕管（1）并基本上从内部（2）覆盖通道（7）的唇缘（9）留下一个狭缝（8）。由于通过通道（7）和狭缝（8）供给的冷却气体在框架（6）上形成表面薄膜，所以本发明要求将支撑框架（6）从热气体中牢固地筛选出来，没有热气流以任何方式受到影响。管（1）特别适合用作燃烧单元中的火焰管，例如。燃气轮机燃烧室。

3. 发明申请

WO1997047925A1 HEAT-SHIELD ARRANGEMENT, ESPECIALLY FOR STRUCTURAL COMPONENTS OF GAS TURBINE PLANTS 审中-公开
标题翻译：热屏蔽装置，尤其是对于燃气轮机设备的结构件
公开(公告)号：WO1997047925A1
公开(公告)日：1997-12-18
申请号：PCT/DE1997001169
申请日：1997-06-10
申请人： SIEMENS AKTIENGESELLSCHAFT , WALZ, Günther , KLEINFELD, Jens , FRANTZHELD, Robert , NEUGEBAUER, Helmut
发明人： SIEMENS AKTIENGESELLSCHAFT
IPC分类号： F23R03/00
CPC分类号： F27D1/04 , F23M5/04 , F23M2900/05004 , F23R3/007 , F27D1/145
摘要： The object of the invention is a heat-shield arrangement to protect a bearing structure (1) from a hot fluid, with an inner cladding (2a) of heat-resistant material and composed of plate-like heat-shield components (2) arranged side-by-side leaving gaps (2b) and anchored to the bearing structure (1) in a manner allowing heat circulation by bolts (4). The heat-shield components (2) are made of a non-eroding and non-corroding material. Between each heat-shield component (2) and the bearing structure (1) is fitted an insulating block (3) of a fireproof ceramic.
摘要翻译：本主题发明涉及并列设置并热可动（上用于保护支撑结构（1）相对于与现有的耐热材料内衬（2a上的热流体），同时留下间隙，其由覆盖的热屏蔽装置的支撑结构（2b）的借助于螺栓锚定1）（4）耐高温，板状热屏蔽元件（2）。热屏蔽元件（2）由一个侵蚀和耐腐蚀的材料制成。每个热屏蔽元件（2）和所述支撑结构（1）之间，各自的绝缘块（3）由布置在耐火陶瓷的。

4. 发明申请

WO1992016798A1 GAS TURBINE ENGINE COMBUSTOR 审中-公开
标题翻译：燃气轮机发动机
公开(公告)号：WO1992016798A1
公开(公告)日：1992-10-01
申请号：PCT/GB1992000201
申请日：1992-02-03
申请人： ROLLS-ROYCE PLC , PIDCOCK, Anthony , COOPER, Stephen, Mark , FRY, Peter
发明人： ROLLS-ROYCE PLC
IPC分类号： F23R03/00
CPC分类号： F23R3/002 , F05B2260/201 , F05B2260/202 , F23R2900/03044
摘要： A gas turbine engine combustor (20) is provided with a wall structure (22) which comprises an outer wall (24) having a plurality of wall elements (26) attached thereto. Each wall element (26) is provided with a flange (27) around its periphery which serves to define a chamber (28) between each wall element (26) and the outer wall (24). Holes (30) in the outer wall (24) permit the flow of cooling air into each chamber (28) to provide impingement cooling of the wall elements (26). Holes (30) in the wall elements (26) permit the exhaustion of cooling air from the chambers (28) to provide film cooling of the wall elements (26).
摘要翻译：燃气涡轮发动机燃烧器（20）设置有壁结构（22），其包括具有附接到其上的多个壁元件（26）的外壁（24）。每个壁元件（26）围绕其周边设置有凸缘（27），其用于限定每个壁元件（26）和外壁（24）之间的腔室（28）。外壁（24）中的孔（30）允许冷却空气流入每个室（28）以提供壁元件（26）的冲击冷却。壁元件（26）中的孔（30）允许从室（28）排出冷却空气以提供壁元件（26）的膜冷却。

5. 发明申请

WO1996018849A1 COMBUSTOR LINER ARRANGEMENT 审中-公开
公开(公告)号：WO1996018849A1
公开(公告)日：1996-06-20
申请号：PCT/US1995015077
申请日：1995-11-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , SULLIVAN, Dennis, J. , BUTLER, Aaron, S. , KELLEY, Mark, A.
IPC分类号： F23R03/00
CPC分类号： F23R3/002 , F05B2260/2241 , F23R3/08
摘要： When second shell section (18) diverges with respect to first shell section (16), the second liner panel (50) is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge (68), and farther from the liner at the downstream end (57). The downstream end of the first liner panel (64) overlaps the second liner panel (50) on the gas side.
摘要翻译：当第二壳部分（18）相对于第一壳部分（16）发散时，第二衬板（50）位于与壳体间距更换的位置。衬套在上游边缘（68）处靠近壳体，并且在下游端（57）处离开衬垫更远。第一衬板（64）的下游端与气体侧的第二衬板（50）重叠。

6. 发明申请

WO1995025932A1 TURBINE COMBUSTOR COOLING SYSTEM 审中-公开
标题翻译：涡轮COMBUSTOR冷却系统
公开(公告)号：WO1995025932A1
公开(公告)日：1995-09-28
申请号：PCT/US1994003138
申请日：1994-03-23
申请人： ALLIEDSIGNAL INC.
发明人： ALLIEDSIGNAL INC. , MYERS, Geoffrey, D. , BOTTLINGER, Judy, P.
IPC分类号： F23R03/00
CPC分类号： F23R3/08 , B23K26/389 , B23K26/40 , B23K2103/50 , F05B2260/202 , F23R3/002 , Y02T50/675
摘要： A gas turbine engine has a low cost combustor liner cooling sytem combining the benefits of high internal heat removal with improved film cooling by employing a large number of strategically positioned, laser-drilled cooling passages (28). Cooling air flows through these specially tailored passages (28) to absorb heat from the liner (20) prior to injection as a protective film on the interior surface. The passages (28) are set in staggered rows on a thickened portion of the liner (20) and have a rough internal heat transfer surface and an exit with a steep injection angle (34B) to evenly distribute the cooling film along the interior surfac of the liner.
摘要翻译：燃气涡轮发动机具有低成本的燃烧器衬管冷却系统，其通过采用大量策略性定位的激光钻孔冷却通道（28）将高内部除热的优点与改进的膜冷却相结合。冷却空气流过这些专门定制的通道（28），以在注射之前吸收来自衬套（20）的热量作为内表面上的保护膜。通道（28）在衬套（20）的加厚部分上以交错排设置，并且具有粗糙的内部传热表面和具有陡峭喷射角（34B）的出口，以使冷却膜沿着内部表面班轮

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