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1. 发明授权

US07669420B2 Fuel injector having an annular prefilmer 有权
标题翻译：燃料喷射器具有环形预压器
公开(公告)号：US07669420B2
公开(公告)日：2010-03-02
申请号：US11482718
申请日：2006-07-10
申请人： Michael P. Spooner
发明人： Michael P. Spooner
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23D11/107 , F23D11/386 , F23D2209/30 , F23D2900/00016 , F23D2900/11101 , F23R3/343
摘要： A fuel injector for a gas turbine engine has a swirl slot that supplies fuel to a prefilmer. The swirl slot has an upstream lip and a downstream lip that are arranged eccentrically. The slot is thus provided with an area of high static pressure and an area of low static pressure caused by the flowing over the eccentrically arranged lips.
摘要翻译：一种用于燃气涡轮发动机的燃料喷射器具有向前置液体供给燃料的涡流槽。涡旋槽具有偏心布置的上游唇缘和下游唇缘。因此，狭槽具有高的静压区域和由偏心偏离的唇缘上流动引起的低静态压力的区域。

2. 发明授权

US07000397B2 Combustion apparatus 有权
公开(公告)号：US07000397B2
公开(公告)日：2006-02-21
申请号：US11020167
申请日：2004-12-27
申请人： Anthony Pidcock , Desmond Close , Michael P Spooner
发明人： Anthony Pidcock , Desmond Close , Michael P Spooner
IPC分类号： F23R3/04
CPC分类号： F23R3/04 , F23R3/002 , F23R2900/03041 , F23R2900/03045
摘要： A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

3. 发明授权

US06708499B2 Combustion apparatus 有权
公开(公告)号：US06708499B2
公开(公告)日：2004-03-23
申请号：US10079403
申请日：2002-02-22
申请人： Anthony Pidcock , Desmond Close , Michael P Spooner
发明人： Anthony Pidcock , Desmond Close , Michael P Spooner
IPC分类号： F23R360
CPC分类号： F23R3/04 , F23R3/002 , F23R2900/03041 , F23R2900/03045
摘要： A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.

4. 发明授权

US06408628B1 Wall elements for gas turbine engine combustors 有权
标题翻译：燃气轮机发动机燃烧器的壁元件
公开(公告)号：US06408628B1
公开(公告)日：2002-06-25
申请号：US09703666
申请日：2000-11-02
申请人： Anthony Pidcock , Desmond Close , Michael P. Spooner
发明人： Anthony Pidcock , Desmond Close , Michael P. Spooner
IPC分类号： F02C100
CPC分类号： F23R3/002 , F23R2900/03044
摘要： A wall element (29A, 29B) for a combustor (20) of a gas turbine engine (10). The wall element (29A, 29B) defines an axis. In use, the axis is arranged generally parallel to the principal axis of the engine (10). In one aspect, the length of the wall element (29B) along the axis is at least substantially 20% of the length of the wall element (29B) transverse to the axis. In another aspect, the wall element (29A, 29B) has a first pair of opposite edges extending transverse to the axis and a second pair of opposite edges (48, 50) extending transverse to the first pair, at least one of the second pair of edges (48, 50) being angled relative to the axis of the wall element (29A, 29B).
摘要翻译：一种用于燃气涡轮发动机（10）的燃烧器（20）的壁元件（29A，29B）。壁元件（29A，29B）限定一个轴线。在使用中，轴线大致平行于发动机（10）的主轴布置。一方面，沿着轴线的壁元件（29B）的长度至少基本上是横向于轴线的壁元件（29B）的长度的20％。在另一方面，壁元件（29A，29B）具有横向于轴线延伸的第一对相对边缘和横向于第一对延伸的第二对相对边缘（48,50），第二对中的至少一个的边缘（48,50）相对于壁元件（29A，29B）的轴线成角度。

5. 发明授权

US08365531B2 Fuel injector 有权
标题翻译：喷油器
公开(公告)号：US08365531B2
公开(公告)日：2013-02-05
申请号：US12312582
申请日：2007-11-19
申请人： Anthony Pidcock , Michael P Spooner
发明人： Anthony Pidcock , Michael P Spooner
IPC分类号： F02C1/00
CPC分类号： F23D11/107 , F23D2900/11101 , F23R3/14 , F23R3/343 , Y02T50/675
摘要： A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.
摘要翻译：一种用于燃气涡轮发动机的燃料喷射头，该喷射头包括先导喷射器和位于导向喷射器径向外侧的主喷射器。一个同心的分配引燃喷射器与主喷射器并限制一个管道，在使用中，引燃喷射器喷射的燃油流过。分流器是中空的以改善冷却，并且具有径向内表面，该径向内表面限定了径向向内逐渐向喉部逐渐变细的第一部分，以及第二部分，其以径向向外的锥度的角度从喉部径向向外渐缩，使得流动在径向内表面上使用的空气保持附着在表面的长度上。

6. 发明授权

US06666025B2 Wall elements for gas turbine engine combustors 有权
标题翻译：燃气轮机发动机燃烧器的壁元件
公开(公告)号：US06666025B2
公开(公告)日：2003-12-23
申请号：US09784162
申请日：2001-02-16
申请人： Michael P Spooner , Anthony Pidcock , Desmond Close
发明人： Michael P Spooner , Anthony Pidcock , Desmond Close
IPC分类号： F23R300
CPC分类号： F23R3/002
摘要： A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.
摘要翻译：一种用于燃气涡轮发动机燃烧器（15）的壁结构（21）的壁元件（29）。壁元件（29）包括具有上游边缘区域（30）和下游边缘区域（31）的主构件（36）。多个散热构件（38）设置在主构件（36）上。壁元件的下游边缘（35）和/或最靠近下游边缘（35）的散热构件的下游侧表面设置有耐热涂层。

7. 发明申请

US20100050644A1 Fuel injector 有权
标题翻译：喷油器
公开(公告)号：US20100050644A1
公开(公告)日：2010-03-04
申请号：US12312582
申请日：2007-11-19
申请人： Anthony Pidcock , Michael P. Spooner
发明人： Anthony Pidcock , Michael P. Spooner
IPC分类号： F02C7/22
CPC分类号： F23D11/107 , F23D2900/11101 , F23R3/14 , F23R3/343 , Y02T50/675
摘要： A fuel injector head for a gas turbine engine the head comprising a pilot injector and a main injector located radially outwardly of the pilot injector. A concentric separates the pilot injector from the main injector and bounding a duct through which in use a fuel injected by the pilot injector flows. The splitter is hollow to improve cooling and has a radially inner surface which defines a first portion which tapers radially inwardly to a throat and a second portion which tapers radially outwardly from the throat with the angle of the radially outwards taper being such that a flow of air in use over the radially inner surface remains attached over the length of the surface.
摘要翻译：一种用于燃气涡轮发动机的燃料喷射头，该喷射头包括先导喷射器和位于导向喷射器径向外侧的主喷射器。一个同心的分配引燃喷射器与主喷射器并限制一个管道，在使用中，引燃喷射器喷射的燃油流过。分流器是中空的以改善冷却，并且具有径向内表面，该径向内表面限定了径向向内逐渐向喉部逐渐变细的第一部分，以及第二部分，其以径向向外的锥度的角度从喉部径向向外渐缩，使得流动在径向内表面上使用的空气保持附着在表面的长度上。

8. 发明授权

US07089742B2 Wall elements for gas turbine engine combustors 有权
标题翻译：燃气轮机发动机燃烧器的壁元件
公开(公告)号：US07089742B2
公开(公告)日：2006-08-15
申请号：US10635482
申请日：2003-08-07
申请人： Michael P. Spooner , Anthony Pidcock , Desmond Close
发明人： Michael P. Spooner , Anthony Pidcock , Desmond Close
IPC分类号： F23R3/00
CPC分类号： F23R3/002
摘要： A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.
摘要翻译：一种用于燃气涡轮发动机燃烧器（15）的壁结构（21）的壁元件（29）。壁元件（29）包括具有上游边缘区域（30）和下游边缘区域（31）的主构件（36）。多个散热构件（38）设置在主构件（36）上。壁元件的下游边缘（35）和/或最靠近下游边缘（35）的散热构件的下游侧表面设置有耐热涂层。

9. 发明授权

US06324830B1 Gas turbine engines 失效
标题翻译：燃气涡轮发动机
公开(公告)号：US06324830B1
公开(公告)日：2001-12-04
申请号：US09672446
申请日：2000-09-29
申请人： Michael P Spooner , Anthony Pidcock , Desmond Close
发明人： Michael P Spooner , Anthony Pidcock , Desmond Close
IPC分类号： F02C200
CPC分类号： F23R3/60
摘要： A fuel injector assembly designed to withstand a predetermined impact load resulting from ingestion of a bird or other foreign object into the combustion stage of a gas turbine engine comprises a body member adapted to be mounted adjacent to and to extend into the combustion chamber and an abutment member disposed downstream of the injector assembly in the direction of air flow through the combustion stage, the arrangement being such that the body member moves into contact with the abutment member when subjected to an impact load in excess of the impact load it is designed to withstand.
摘要翻译：设计成承受由鸟或其他异物摄取到燃气涡轮发动机的燃烧阶段而产生的预定冲击载荷的燃料喷射器组件包括适于安装在燃烧室附近并延伸到燃烧室中的主体部件，在喷射器组件的下游设置在通过燃烧级的空气流动的方向上的构件，该构造使得当受到冲击载荷超过其被设计为承受的冲击载荷时，本体构件与抵靠构件接触移动。

10. 发明授权

US06857275B2 Combustion apparatus 有权
标题翻译：燃烧装置
公开(公告)号：US06857275B2
公开(公告)日：2005-02-22
申请号：US10688875
申请日：2003-10-21
申请人： Anthony Pidcock , Desmond Close , Michael P. Spooner
发明人： Anthony Pidcock , Desmond Close , Michael P. Spooner
IPC分类号： F23R3/00 , F23R3/04 , F02C3/60
CPC分类号： F23R3/04 , F23R3/002 , F23R2900/03041 , F23R2900/03045
摘要： A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.
摘要翻译：用作燃气涡轮发动机燃烧器壁结构的内壁的一部分的壁元件是铸造结构，并且包括多个设置在其中并通过铸造过程形成的冷却孔。冷却孔可以位于它们不能通过激光钻孔通常形成的位置。

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