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1. 发明公开

EP0042217A3 Fuel inlet assemblies for fuel reactors 失效
标题翻译：用于燃料反应器的燃油进口组件
公开(公告)号：EP0042217A3
公开(公告)日：1982-10-13
申请号：EP81302230
申请日：1981-05-19
申请人： BS & B ENGINEERING COMPANY INC.
发明人： Markus, Gerardus Anthonius
IPC分类号： F23R03/10
CPC分类号： F23C3/00 , F23C7/06
摘要： A fuel inlet assembly for a fuel reactor which has an inner shell mounted coaxially within an outer shell, which is closed-at one axial end, the outer shell having an inlet for introducing combustion air into the annular space between the inner and outer shells, the other end of the inner shell being spaced from the inlet assembly which is mounted at the other end of the outer shell, the fuel inlet assembly including a base plate which is mountable on said other end of the outer shell, and having a fuel inlet aperture therein. A first frusto-conical inlet cone is mounted on the base plate to surround the fuel inlet aperture and a second frusto-conical inlet cone is mounted coaxially therewith by means of a plurality of circumferentially spaced wanes which extend in radial planes, the second cone overlapping the first cone, whereby a portion of the combustion air can flow through the annular space between the first and second inlet cones, with an axial component of velocity, to premix with the fuel entering at the first fuel inlet aperture.

2. 发明公开

EP0078630A3 Fuel nozzle assembly for a gas turbine engine 失效
标题翻译：燃气喷气发动机燃油喷嘴组件
公开(公告)号：EP0078630A3
公开(公告)日：1983-08-10
申请号：EP82305561
申请日：1982-10-19
申请人： AVCO CORPORATION
发明人： Ben-Porat, Avi
IPC分类号： F23R03/10 , F23R03/60
CPC分类号： F23R3/10 , F23R3/283 , F23R3/60 , Y02T50/675
摘要： A self-aligning fuel nozzle assembly 34 maintains the alignment of a swirler member 30 and a fuel nozzle 18 upon displacement of the combustor liner 24 relative to the combustor housing 12 of a combustion chamber assembly in a turbine engine 10. The selfaligning fuel nozzle assembly 34 mounts the swirler member 30 to the combustor liner 24 by a device having six degrees of freedom including a ball and socket joint 44,50 which is placed within a structure so as to permit movement in the three main Cartesian directions of a rectangular axis system. The combustor liner 24 is installed within the combustor housing 12 in such manner that the fuel nozzle 18 is slidably received within the swirler 30, with the swirler 30 being biased against the fuel nozzle 18 by a helical spring member 96 forming part of the assembly. The assembly 34 is slidably mounted between plates 74, 76 on the liner 24 to allow side to side and up and down relative movement of the liner 24 and housing 12. The self-aligning fuel nozzle assembly 34 reduces the development of local stresses between the swirler 30 and the fuel nozzle so that wearing between these parts is reduced. The swirler member 30 and fuel nozzle are retained in aligned positions so that the self-aligning fuel nozzle assembly 34 promotes improved fuel economy in the engine.

3. 发明申请

WO1996018853A1 FUEL NOZZLE GUIDE RETAINER ASSEMBLY 审中-公开
标题翻译：燃油喷嘴指南保持器组件
公开(公告)号：WO1996018853A1
公开(公告)日：1996-06-20
申请号：PCT/US1995015569
申请日：1995-11-29
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , JOHNSON, Thomas, E.
IPC分类号： F23R03/10
CPC分类号： F23R3/283 , F23R3/10
摘要： Fuel nozzle guide (24) is threaded to fuel nozzle retainer (26), entrapping bulkhead (14), bulkhead liner (30) and key washer (28). Internal tabs (74) lock within slot (76) in the threads of the fuel nozzle guide. External tabs (78) of the key washer are bent into slot (80) of the retainer (26), after the nozzle guide (24) and the retainer are threaded together.
摘要翻译：燃料喷嘴引导件（24）被螺纹连接到燃料喷嘴保持器（26），截留隔板（14），隔板衬套（30）和钥匙垫圈（28）。内部突片（74）锁定在燃料喷嘴引导件的螺纹中的槽（76）内。在喷嘴引导件（24）和保持器拧在一起之后，钥匙圈的外部卡舌（78）弯曲到保持器（26）的槽（80）中。

4. 发明申请

WO1996027765A1 THERMAL SHIELD ARRANGEMENT FOR GAS TURBINE COMBUSTION CHAMBERS 审中-公开
标题翻译：热屏蔽装置的燃气涡轮燃烧
公开(公告)号：WO1996027765A1
公开(公告)日：1996-09-12
申请号：PCT/EP1996000860
申请日：1996-03-01
申请人： BMW ROLLS-ROYCE GMBH , KWAN, William
发明人： BMW ROLLS-ROYCE GMBH
IPC分类号： F23R03/10
CPC分类号： F23R3/283 , F23R3/10
摘要： In order to cool down as efficiently as possible the hot surface of the thermal shield (1) that surrounds the burner of a gas turbine ring-shaped combustion chamber, in particular in the area of the burner outlet (3), a cooling air flow (10) ejected in the direction of the outlet over a continuous web (8) at the edge of the outlet is guided by a guiding rib (9). The guiding rib (9) is substantially parallel to the web (8) and has at the side of the combustion chamber a bent end, so that the cooling air flow that enters the gap between the web and the guiding rib is deflected there towards the hot surface (2b) of the thermal shield (1).
摘要翻译：为了尽可能有效地进行冷却，冷却空气流（10）在所述通道开口幅的周缘的燃气涡轮机环形燃烧室隔热屏（1），特别是在燃烧器开口（3）的区域的周围的燃烧器的热表面（8）出口在通道开口的方向，通过一个导向肋（9）进行。此导向肋（9）被定向为平行于所述幅材（8）基本上与燃烧室侧具有到热表面的方向上的冷却空气流有卷筒纸和引导肋之间的间隙的流入（2b）中的防热罩（1）被偏转这样的弯曲端，

5. 发明申请

WO1992019915A1 COMBUSTION CHAMBER ASSEMBLY IN A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气轮机组合在燃气涡轮发动机中
公开(公告)号：WO1992019915A1
公开(公告)日：1992-11-12
申请号：PCT/GB1992000745
申请日：1992-04-23
申请人： ROLLS-ROYCE PLC , BURNELL, Anthony, David , PRICE, Peter, David
发明人： ROLLS-ROYCE PLC
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , Y02T50/675
摘要： Overrich regions of fuel mixture in the combustion chamber of a gas turbine engine are dispersed by a jet of air directed into the region. Plumes of fuel/air mixture from adjacent airspray burners overlap to create overrich regions which tend to produce soot. Aligned apertures (20) in the head of the combustion chamber direct jets of high pressure air at the regions with as little loss of momentum as possible, to disperse them. The apertures (20) may be in the form of slots to provide fan-shaped jets.

6. 发明申请

WO1996018851A1 SEGMENTED BULKHEAD LINER 审中-公开
公开(公告)号：WO1996018851A1
公开(公告)日：1996-06-20
申请号：PCT/US1995015095
申请日：1995-11-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , JOHNSON, Thomas, E. , MADDEN, Thomas, J. , SODERQUIST, Robert, W.
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , F23R3/283 , F23R3/50
摘要： Truncated pie shaped bulkhead liner sections (60) are each divided into two liner segments (62). The division occurs adjacent fuel nozzle opening (20). Upstream extending lips (71, 75 and 77) abut the bulkhead (14). Cooling air passes through cooling flow openings in the bulkhead with all the flow continuing toward the shell (38, 40) edges of the liner segments.
摘要翻译：截断的饼形隔板衬套部分（60）分别分成两个衬垫段（62）。分界面邻近燃料喷嘴开口（20）发生。上游延伸唇缘（71,75和77）邻接舱壁（14）。冷却空气通过隔板中的冷却流动开口，其中所有的流体都朝着衬套段的壳体（38,40）的边缘继续。

7. 发明申请

WO1992021919A1 GAS TURBINE ENGINE COMBUSTOR 审中-公开
标题翻译：燃气轮机发动机
公开(公告)号：WO1992021919A1
公开(公告)日：1992-12-10
申请号：PCT/GB1992000667
申请日：1992-04-13
申请人： ROLLS-ROYCE PLC , HARRISON, Andrew , PARK, Keith
发明人： ROLLS-ROYCE PLC
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , Y02T50/675
摘要： A gas turbine engine combustor (16) is provided with an airspray fuel injector (24), the downstream end of which is coplanar with a heat shield (38) provided at the upstream end of the combustor (16). The fuel injector (24) injects a fuel and air mixture into the combustion chamber (16a) defined within the combustor (16) which is in the form of a cone having an angle of greater than 130 DEG . The combustor (16) has enhanced weak extinction characteristics.
摘要翻译：燃气涡轮发动机燃烧器（16）设置有喷气燃料喷射器（24），其下游端与设置在燃烧器（16）的上游端的隔热罩（38）共面。燃料喷射器（24）将燃料和空气混合物喷射到限定在燃烧器（16）内的形成角度大于130°的锥形的燃烧室（16a）中。燃烧器（16）具有增强的弱消光特性。

8. 发明申请

WO1996023175A1 HEAT SHIELD FOR A GAS TURBINE COMBUSTION CHAMBER 审中-公开
标题翻译：隔热板用于燃气轮机燃烧室
公开(公告)号：WO1996023175A1
公开(公告)日：1996-08-01
申请号：PCT/EP1996000300
申请日：1996-01-25
申请人： BMW ROLLS-ROYCE GMBH , KWAN, William
发明人： BMW ROLLS-ROYCE GMBH
IPC分类号： F23R03/10
CPC分类号： F23R3/50 , F23R3/10 , F23R2900/03041 , F23R2900/03042
摘要： A heat shield for a gas turbine annular combustion chamber having a plurality of effusion holes, the central axes of which are inclined towards the heat shield surface and over which cooling air can penetrate from the rear to apply a film of cooling air to the hot surface. The surface is subdivided into sectors and transition areas between the sectors, the central axes of the effusion holes essentially being arranged in parallel to each other in a given sector or transition area. In addition, the central axes of the effusion holes in the sectors are oriented towards the assigned corner area in each case.
摘要翻译：一种热屏蔽件为具有多个泻流孔，其中心轴线是倾斜的，以热屏蔽表面，并且可以从后侧穿过该冷却空气的冷却空气薄膜放置到热表面上的燃气涡轮的环形燃烧器。在区段中，过渡区之间的位于所述扇区的表面被分开，其特征在于，所述积液的孔的中心轴基本上与在扇区或在过渡区域中的每个的情况下相互平行排列。在扇区中的泻流孔具有超出朝向每个所述热屏蔽的相关联的角部区域的中心轴。

9. 发明申请

WO1996018852A1 BULKHEAD LINER WITH RAISED LIP 审中-公开
标题翻译：大型衬里与升级LIP
公开(公告)号：WO1996018852A1
公开(公告)日：1996-06-20
申请号：PCT/US1995015412
申请日：1995-11-30
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , JOHNSON, Thomas, E.
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , F23R3/283
摘要： Bulkhead (14) is conical and therefor the surface of bulkhead liners (30) has a curved or arcuate surface. Raised lip (70) with planar surface (72) is adjacent and surrounded in each opening (20). Fuel nozzle guide (24) may be rotated against and sealed to the surface of the liner segments.
摘要翻译：隔板（14）是圆锥形的，因此舱壁衬垫（30）的表面具有弯曲或弓形表面。具有平坦表面（72）的凸起唇缘（70）在每个开口（20）中相邻并包围。燃料喷嘴引导件（24）可以旋转并且密封到衬套段的表面。

10. 发明申请

WO1996018850A1 BULKHEAD COOLING FAIRING 审中-公开
标题翻译：大理石冷却公路
公开(公告)号：WO1996018850A1
公开(公告)日：1996-06-20
申请号：PCT/US1995014406
申请日：1995-11-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , JOHNSON, Thomas, E. , THOMPSON, Craig, G.
IPC分类号： F23R03/10
CPC分类号： F23R3/10 , F23R3/283
摘要： Cooling air flow from behind bulkhead liner segments (30) and from behind float wall panels (42) is guided as flow (50) over the hot surface of the bulkhead liner segments by fairing (44). The fairing is secured between a shell (38, 40) and a float wall panel (42), and being of equal and coincident length as the panel, may be replaced with the removal of only one panel.
摘要翻译：舱壁衬垫段（30）后面和浮动墙板（42）之后的冷却空气流通过整流罩（44）作为流体（50）被引导到舱壁衬套段的热表面上。整流罩固定在壳体（38,40）和浮动壁板（42）之间，并且具有与面板相同和重合的长度，可以用仅一个面板的移除来代替。

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