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1.发明授权
公开(公告)号：US5285630A
公开(公告)日：1994-02-15
申请号：US978819
申请日：1992-11-19
CPC分类号： F23R3/26 , F23R3/04 , Y02T50/675
摘要： A system for reducing nitrogen oxide emissions from a gas turbine engine is disclosed in which a portion of air in the air compressor is tapped and supplied to an inlet which introduces at least a portion of the tapped air into the primary zone of the combustion chamber. A control device is disposed between the tap and the inlet to control the air flow passing to the inlet. The inlet is located so as to inject the tapped air into the combustion chamber primary zone at the intersection of adjacent fuel sprays. The control device, which may be an adjustable flap valve or a three-way valve, may also be operatively connected to the throttle control for the gas turbine engine such that the control allows the maximum amount of air to pass into the combustion chamber under full power conditions. The control device is preferably mounted outside the engine casing enclosing the combustion chamber to allow easy access for assembly and maintenance.
摘要翻译： 本发明涉及一种涡轮发动机，其包括由相同空气流连续进给的压缩机（1），燃烧室（2）和涡轮机（3），并且还包括适于减少所述氮气氧化物形成的装置 燃烧室。 该装置包括用于取出由压缩机（1）输送的空气的一部分的装置（9a，9b），用于引入在从两个相邻碗排出的燃料锥体的交点处获取的一部分空气的装置（21） 以及用于控制作为发动机转速的函数的在燃料圆锥的交点处引入的空气流的控制装置（10）。
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公开(公告)号：US4766722A
公开(公告)日：1988-08-30
申请号：US890474
申请日：1986-07-30
CPC分类号： F23R3/26 , F23C7/02 , F23D11/10 , F23R3/10 , F05B2250/411 , F23D2900/11101 , Y02T50/675
摘要： A fuel system for a turbojet engine is disclosed in which the operating parameters of the engine are improved throughout the range of engine operating conditions. The fuel system includes an enlarged intermediate bowl for the combustion chamber which increases the reactive volume, while at the same time provides sufficient cooling of the bowl to avoid burn-through or uneven engine operating characteristics. The bowl extends radially outwardly beyond an opening in the base of the combustion chamber and defines a row of air inlet orifices which serves to more completely atomize the fuel prior to its ignition. A diaphragm control system may also be utilized to control the amount of air flowing into the bowl as the engine speed changes.
摘要翻译： 公开了一种用于涡轮喷气发动机的燃料系统，其中发动机的运行参数在发动机运行条件的整个范围内得到改善。 燃料系统包括用于燃烧室的扩大的中间碗，其增加了反应体积，同时提供了足够的碗的冷却，以避免燃烧或不均匀的发动机操作特性。 该碗径向向外延伸超过燃烧室底部的开口，并且限定了一排空气入口孔，其用于在点火之前更完全地使燃料雾化。 当发动机转速变化时，还可以使用隔膜控制系统来控制流入碗中的空气量。
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公开(公告)号：US5598697A
公开(公告)日：1997-02-04
申请号：US505633
申请日：1995-07-21
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F05B2260/201 , F05B2260/202 , F05B2260/222
摘要： A wall structure for a wall bounding a combustion chamber of a gas turbine engine is disclosed having a first wall with an inner surface facing towards the interior of the combustion chamber and an outer surface facing away from the interior of the combustion chamber such that the inner surface forms a boundary of the combustion chamber and the outer surface has a surface roughness to prevent the formation of a fluid flow cooling layer which would cool the outer surface. The invention also has a second wall spaced from the outer surface of the first wall in a direction away from the interior of the combustion chamber so as to define a cooling fluid circulatory space between the first and second walls. A plurality of first perforations extend through the first wall in communication with the cooling fluid circulatory space to enable passage of cooling fluid from the space through the first perforations to form a cooling fluid film on the inner surface of the first wall.
摘要翻译： 公开了一种用于限定燃气涡轮发动机的燃烧室的壁的壁结构，其具有面向燃烧室内部的内表面的第一壁和远离燃烧室内部的外表面， 表面形成燃烧室的边界，并且外表面具有表面粗糙度，以防止形成冷却外表面的流体流动冷却层。 本发明还具有在远离燃烧室内部的方向上与第一壁的外表面隔开的第二壁，以便限定第一和第二壁之间的冷却流体循环空间。 多个第一穿孔延伸穿过与冷却流体循环空间连通的第一壁，以使冷却流体能够从空间通过第一穿孔，以在第一壁的内表面上形成冷却流体膜。
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公开(公告)号：US5341645A
公开(公告)日：1994-08-30
申请号：US44388
申请日：1993-04-08
CPC分类号： F23R3/20 , F23R3/30 , F23D2900/11001
摘要： A fuel/oxidizer pre-mixing combustion chamber for a turbojet engine is disclosed in which the pre-mixing device is incorporated into the upstream end wall structure of the combustion chamber. The upstream end portion of the combustion chamber, which is in communication with the oxidizer, has a plurality of generally radially extending, "V"-shaped members oriented such that the vertex of the "V" shape faces in an upstream direction. These members extend generally radially between the inner and outer walls which define the boundaries of the combustion chamber. The members define upstream edges and downstream edges which are axially the upstream edges. Fuel injectors extend radially inwardly between these members and are axially positioned between the locations of the upstream and downstream edges so as to spray fuel onto the adjacent sides of each of the members. The downstream edges of the members are circumferentially spaced apart so as to define a passage which is in communication with the oxidizer source and the combustion chamber.
摘要翻译： 公开了一种用于涡轮喷气发动机的燃料/氧化剂预混合燃烧室，其中预混合装置结合到燃烧室的上游端壁结构中。 与氧化剂连通的燃烧室的上游端部具有多个大致径向延伸的“V”形构件，其定向为使得“V”形顶点朝向上游方向。 这些构件在限定燃烧室的边界的内壁和外壁之间大致径向地延伸。 这些构件限定了沿着上游边缘的上游边缘和下游边缘。 燃料喷射器在这些构件之间径向向内延伸并且轴向地定位在上游和下游边缘的位置之间，以便将燃料喷射到每个构件的相邻侧面上。 构件的下游边缘周向间隔开，以便限定与氧化剂源和燃烧室连通的通道。
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公开(公告)号：US5634328A
公开(公告)日：1997-06-03
申请号：US561335
申请日：1995-11-21
IPC分类号： F23R3/34
CPC分类号： F23R3/34
摘要： A method of supplying fuel to a combustion chamber of a turbojet engine having a low power head with a plurality of low power fuel injectors and a high power head having a plurality of high power fuel injectors is disclosed in which fuel is supplied to the plurality of low power fuel injectors during low power operation of the engine, fuel is supplied to a first fuel circuit in the plurality of high power fuel injectors during high power operation of the turbojet engine and fuel is also supplied to a second fuel circuit in the plurality of high power fuel injectors during low power operation of the turbojet engine, the second fuel circuit being separate from the first fuel circuit. This method of supplying fuel to the dual head combustion chamber optimizes operation of the combustion chamber in all modes of engine operation.
摘要翻译： 公开了一种向具有多个低功率燃料喷射器的低功率头的涡轮喷气发动机的燃烧室供给燃料的方法和具有多个高功率燃料喷射器的高功率头，其中向多个 在发动机的低功率运行期间，低功率燃料喷射器在涡轮喷气发动机的高功率操作期间向多个大功率燃料喷射器中的第一燃料回路供应燃料，并且燃料也被供给到多个涡轮喷气发动机中的第二燃料回路 所述高功率燃料喷射器在所述涡轮喷气发动机的低功率运行期间，所述第二燃料回路与所述第一燃料回路分离。 这种向双头燃烧室供应燃料的方法优化了在所有发动机运行模式下燃烧室的运行。
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6.发明授权
公开(公告)号：US5351475A
公开(公告)日：1994-10-04
申请号：US136263
申请日：1993-10-15
摘要： A fuel injection system is disclosed which incorporates a plurality of bowl or shroud members extending upstream of an end wall of the combustion chamber between the end wall and an air swirler in which the shroud member has an end joined with the end wall of the combustion chamber having a substantially elongated elliptical cross-sectional configuration. The end wall of the combustion chamber defines an elliptical shaped opening corresponding to the shape of the end of the shroud or bowl member to enable the fuel/air mixture to be atomized as it enters the combustion chamber. The bowl or shroud member may also define a plurality of openings to enable additional air to be mixed with atomized fuel cone.
摘要翻译： 公开了一种燃料喷射系统，其包括在端壁和空气旋流器之间延伸的燃烧室的端壁的上游延伸的多个碗或护罩构件，其中护罩构件具有与燃烧室的端壁连接的端部 具有基本上细长的椭圆形横截面构造。 燃烧室的端壁限定对应于护罩或碗构件的端部的形状的椭圆形开口，以使燃料/空气混合物在进入燃烧室时被雾化。 碗或护罩构件还可以限定多个开口，以使额外的空气与雾化的燃料锥体混合。
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公开(公告)号：US5311743A
公开(公告)日：1994-05-17
申请号：US059752
申请日：1993-05-12
IPC分类号： F23R3/34
CPC分类号： F23R3/34
摘要： A gas separation assembly for a gas turbine engine combustion chamber is disclosed having spaced apart partition walls which extend through an end of the combustion chamber so as to define an oxidizer chamber which communicates with a source of oxidizer. Downstream ends of the spaced apart partition walls within the combustion chamber are interconnected to a plurality of generally "V" shaped spacers oriented such that the apex of the "V" configuration faces toward the end of the combustion chamber. Downstream edges of the partition walls are notched, also in a "V" shaped configuration such that the notches extend between opposite legs of the spacers. The spacers are circumferentially spaced apart so as to define passageways which communicate with the oxidizer chamber to enable oxidizer to pass through the gas separation assembly into the combustion chamber. The notches in the downstream edges of the partition walls form a series of generally radially extending flues to facilitate heat transfer between the combustion zones by convection. The design also eliminates the hot spots of the known prior art separation assemblies.
摘要翻译： 公开了一种用于燃气涡轮发动机燃烧室的气体分离组件，其具有间隔开的分隔壁，其延伸穿过燃烧室的端部，以便限定与氧化剂源连通的氧化器室。 在燃烧室内的间隔开的分隔壁的下游端部与多个大体上为“V”形的间隔物相互连接，使得“V”构型的顶点朝向燃烧室的端部。 分隔壁的下游边缘也是“V”形构造的凹口，使得凹口在间隔物的相对腿之间延伸。 间隔件沿周向间隔开，以便限定与氧化器室连通的通道，以使氧化剂能够通过气体分离组件进入燃烧室。 分隔壁的下游边缘中的凹口形成一系列通常径向延伸的通道，以便于通过对流在燃烧区域之间的热传递。 该设计还消除了已知现有技术的分离组件的热点。
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8.发明授权
公开(公告)号：US5528896A
公开(公告)日：1996-06-25
申请号：US337537
申请日：1994-11-09
申请人： Jean-Paul D. Alary , Michel A. A. Desaulty , Joe L. Jamet , Denis J. M. Sandelis , Pierre M. V. Schroer
发明人： Jean-Paul D. Alary , Michel A. A. Desaulty , Joe L. Jamet , Denis J. M. Sandelis , Pierre M. V. Schroer
CPC分类号： F23R3/34 , F23R3/12 , Y02T50/675
摘要： A gas flow separator for an annular combustion chamber of a gas turbine engine is disclosed in which the radially spaced apart first and second gas flow separator walls which extend axially into the combustion chamber from the combustion chamber upstream end wall each define a plurality of axially extending channels. Each of the channels extends generally axially in an upstream direction from the downstream edge of each of the separator walls such that their axial lengths are less than the axial lengths of the respective separator walls. Both the depth and the width of each of the channels increases from its upstream end point to the downstream edges of the separator walls. The channels may be circumferentially aligned with each other, or the channels of one separator wall may be circumferentially offset from the channels of the other separator wall.
摘要翻译： 公开了一种用于燃气涡轮发动机的环形燃烧室的气流分离器，其中径向间隔开的第一和第二气流分离器壁从燃烧室上游端壁轴向延伸到燃烧室中，每个限定多个轴向延伸的 频道 每个通道从每个分隔壁的下游边缘沿上游方向大致轴向地延伸，使得它们的轴向长度小于相应分隔壁的轴向长度。 每个通道的深度和宽度都从其上游端点到分隔壁的下游边缘增加。 通道可以彼此周向对齐，或者一个分隔壁的通道可以沿着另一分隔壁的通道周向偏移。
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9.发明授权
公开(公告)号：US5592821A
公开(公告)日：1997-01-14
申请号：US523908
申请日：1995-09-06
申请人： Jean-Paul D. Alary , Gerard Y. G. Barbier , Corine G. Delahaye , Jacques G. W. R. Havard , Paul Mackovic , Bruno R. H. Masse , Didier Merville , Francois J.-P. Mirville , Serge R. Y. Muccioli , Denis J. M. Sandelis , Ralph M. Stelter
发明人： Jean-Paul D. Alary , Gerard Y. G. Barbier , Corine G. Delahaye , Jacques G. W. R. Havard , Paul Mackovic , Bruno R. H. Masse , Didier Merville , Francois J.-P. Mirville , Serge R. Y. Muccioli , Denis J. M. Sandelis , Ralph M. Stelter
CPC分类号： F23R3/04 , F04D29/544 , Y02T50/675
摘要： A separator-diffuser for a gas turbine engine is disclosed wherein the diffuser includes axial walls which function as a guide vane stage for the oxidizer compressor. By incorporating the last, or downstream, guide vane stage into the diffuser structure, the overall axial length and bulk of the gas turbine engine may be significantly reduced. The separator-diffuser has a wall defining a generally annular oxidizer flow passage extending around the central axis of the gas turbine engine, the passage having an oxidizer inlet located downstream of the last rotor stage of the oxidizer compressor so as to enable the oxidizer to pass from the oxidizer compressor into the oxidizer flow passage. A generally annular separator member is located in the oxidizer flow passage downstream of the oxidizer inlet so as to divide the oxidizer flow passage into at least two separate oxidizer flow paths, each flow path having a separate oxidizer outlet. The oxidizer outlets are positioned so as to direct the oxidizer towards one of the annular array of fuel injection heads. A plurality of circumferentially spaced apart, axially extending primary arms connect the separator member to the diffuser walls so as to support the separator within the oxidizer passageway and to serve as a guide vane stage for the oxidizer emanating from the oxidizer compressor.
摘要翻译： 公开了一种用于燃气涡轮发动机的分离器扩散器，其中扩散器包括用作氧化剂压缩机的导叶台的轴向壁。 通过将最后的或下游的引导叶片级结合到扩散器结构中，燃料涡轮发动机的整体轴向长度和体积可以显着减小。 分离器 - 扩散器具有限定围绕燃气涡轮发动机的中心轴线延伸的大致环形的氧化剂流动通道的壁，该通道具有位于氧化剂压缩机的最后转子级的下游的氧化剂入口，以使氧化剂能够通过 从氧化剂压缩机进入氧化剂流通道。 大体上环形的分离器构件位于氧化剂入口下游的氧化剂流动通道中，以便将氧化剂流动通道分成至少两个单独的氧化剂流动路径，每个流动路径都具有单独的氧化剂出口。 氧化剂出口定位成将氧化剂引向燃料喷射头的环形阵列之一。 多个周向间隔开的轴向延伸的主臂将分离器构件连接到扩散器壁，以便将分离器支撑在氧化剂通道内并用作用于从氧化剂压缩机发出的氧化剂的导叶台。
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10.发明授权System for supplying fuel to and cooling a fuel injector of a dual head combustion chamber 失效用于向双头燃烧室的燃料喷射器供应燃料和冷却燃料喷射器的系统
公开(公告)号：US5568721A
公开(公告)日：1996-10-29
申请号：US492567
申请日：1995-06-30
摘要： The present invention relates to a method and apparatus for supplying fuel to and cooling a fuel injector of a gas turbine engine having a dual head combustion chamber. The method comprises the steps of supplying a total fuel flow to the fuel injector such that at least a portion of the total fuel flow circulates through the high power injector nozzle during all operational modes of the gas turbine engine, including those modes in which the high power injector is not supplying fuel to the combustion chamber, and evacuating unused fuel from the high power injector. The apparatus includes a fuel supply conduit connected to the high power injector to supply at least a portion of the total fuel flow supplied to the fuel injector to the high power injector during all operational modes of the gas turbine engine; a fuel control valve to control the amount of fuel flowing through the fuel injector orifices; and a fuel evacuation conduit connected to the high power injector so as to evacuate unused fuel from the high power injector.
摘要翻译： 本发明涉及一种用于向具有双头燃烧室的燃气涡轮发动机的燃料喷射器供给和冷却燃料的方法和装置。 该方法包括以下步骤：向燃料喷射器供应总燃料流，使得在燃气涡轮发动机的所有操作模式期间，总燃料流的至少一部分循环通过高功率喷射器喷嘴，包括其中高 动力注射器不向燃烧室供应燃料，并且从大功率注射器排出未使用的燃料。 该装置包括连接到大功率注射器的燃料供应管道，以在燃气涡轮发动机的所有操作模式期间将供应到燃料喷射器的总燃料流量的至少一部分提供给高功率喷射器; 燃料控制阀，用于控制流过燃料喷射器孔的燃料量; 以及连接到大功率注射器以从大功率注射器排出未使用的燃料的燃料排出导管。
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