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公开(公告)号：US5592819A
公开(公告)日：1997-01-14
申请号：US400574
申请日：1995-03-08
申请人： Denis R. H. Ansart , Patrice A. Commaret , Etienne S. R. David , Michel A. A. Desaulty , Bruno M. M. Quinquenneau , Denis Sandelis
发明人： Denis R. H. Ansart , Patrice A. Commaret , Etienne S. R. David , Michel A. A. Desaulty , Bruno M. M. Quinquenneau , Denis Sandelis
CPC分类号： F23R3/12 , F23R3/286 , F23R3/32 , Y02T50/675
摘要： A pre-mixing injection system to feed a fuel/air mixture to a combustion zone in a turbojet engine combustion chamber is disclosed having a pre-mixing tube defining a convergent pre-mixing zone and a diverging intermediate zone between the fuel and air injection devices, and the combustion zone of the combustion chamber. The convergent pre-mixing zone has an inlet adjacent to the fuel injector and air swirlers to accept the fuel/air mixture into the pre-mixing tube. The pre-mixing zone converges in a direction from the inlet to an outlet which is in communication with the inlet of the divergent intermediate zone. The divergent intermediate zone has an outlet which is, in turn, in communication with the combustion zone of the turbojet engine combustion chamber. The divergent intermediate zone is defined by an inner wall and an outer wall spaced from the inner wall so as to define a generally frusto-conical chamber between them. The outer wall has a plurality of cooling holes to enable cooling air to pass through the outer wall into cooling contact with the inner wall. The frusto-conical chamber has a downstream evacuation passage to allow cooling air to pass from the frusto-conical chamber.
摘要翻译： 公开了一种用于将燃料/空气混合物供给到涡轮喷气发动机燃烧室中的燃烧区域的预混合喷射系统，其具有限定会聚预混合区域的预混合管和燃料和空气喷射装置之间的发散中间区域 和燃烧室的燃烧区域。 会聚预混合区域具有与燃料喷射器相邻的入口和空气旋流器以将燃料/空气混合物接收到预混合管中。 预混合区在从入口到与发散中间区的入口连通的出口的方向会聚。 发散中间区域具有出口，该出口又与涡轮喷气发动机燃烧室的燃烧区域连通。 发散中间区由内壁和与内壁隔开的外壁限定，以便在它们之间限定一个大致截头圆锥形的室。 外壁具有多个冷却孔，以使冷却空气能够通过外壁与内壁冷却接触。 截头圆锥室具有下游排气通道，以允许冷却空气从截头圆锥室通过。
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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：US5590531A
公开(公告)日：1997-01-07
申请号：US355474
申请日：1994-12-14
CPC分类号： F23R3/002 , F05B2200/31
摘要： A wall structure for a gas turbine engine structure, such as a combustion chamber or an afterburner duct is disclosed having a plurality of cooling orifices formed through the wall located in a plurality of odd and even transverse rows, each row having a plurality of cooling orifices located in a plane extending substantially perpendicular to a longitudinal axis of symmetry with the cooling orifices of each odd and even row being circumferentially offset from the cooling orifices of the adjacent upstream corresponding odd and even row. The cooling orifices have a common diameter D and are circumferentially offset a distance d such that distance d is between 0.5 D and D. The axes of the orifices in the odd numbered rows lie on a first main line extending obliquely to the longitudinal axis of symmetry and to the oxidizer air flow, and the axes of orifices on the even numbered rows lie on a second main line, also extending obliquely to the longitudinal axis of symmetry and to the oxidizer air flow. The axes of the orifices in the adjacent rows lie on secondary lines which extend obliquely to the first and second main lines and also to the longitudinal axis of symmetry. Any weld joints necessary to form the annular combustion chamber or afterburner duct from a plurality of wall segments extend parallel to the secondary lines and may be spaced equidistantly from adjacent secondary lines.
摘要翻译： 公开了一种用于燃气涡轮发动机结构的壁结构，例如燃烧室或后燃器管，其具有多个通过位于多个奇数和均匀横向行中的壁形成的冷却孔，每排具有多个冷却孔 位于基本上垂直于纵向对称轴延伸的平面中，每个奇数和偶数行的冷却孔周向地偏离相邻上游相应的奇数和偶数行的冷却孔。 冷却孔具有共同的直径D，并且在周向上偏离距离d，使得距离d在0.5D和D之间。奇数行中的孔的轴位于相对于纵向对称轴线倾斜延伸的第一主线 和氧化剂空气流，并且偶数行上的孔的轴线位于第二主线上，其也垂直于纵向对称轴线和氧化剂空气流延伸。 相邻行中的孔的轴线位于相对于第一和第二主线倾斜延伸并且还延伸到纵向对称轴线的次级线上。 从多个壁段形成环形燃烧室或后燃器管道所需的任何焊接接头平行于次级管线延伸，并且可以与相邻次级管线等间距地间隔开。
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4.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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公开(公告)号：US4696157A
公开(公告)日：1987-09-29
申请号：US919126
申请日：1986-10-15
申请人： Gerard Y. G. Barbier , Gerald J. P. B. Leboure , Michel A. A. Desaulty , Rodolphe Martinez , Jerome Perigne
发明人： Gerard Y. G. Barbier , Gerald J. P. B. Leboure , Michel A. A. Desaulty , Rodolphe Martinez , Jerome Perigne
摘要： A fuel and air injection system for a turbojet engine is disclosed wherein a bowl-shaped member surrounding the fuel injection nozzle defines an impact cooling chamber divided into four sectors. A pair of diametrically opposite sectors have openings to permit air to pass through the cooling chamber into the combustion chamber, while opposite diametrically opposed sectors have openings of larger diameter which also allow communication between the cooling chamber and the combustion chamber. A diaphragm control system allows the air passing into the sectors having the larger diameter openings to be modulated depending upon the throttle setting of the turbojet engine.
摘要翻译： 公开了一种用于涡轮喷气发动机的燃料和空气喷射系统，其中包围燃料喷射喷嘴的碗状部件限定了被分成四个扇区的冲击冷却室。 一对直径相对的扇区具有允许空气通过冷却室进入燃烧室的开口，而相对的直径相对的扇区具有较大直径的开口，其还允许冷却室和燃烧室之间的连通。 隔膜控制系统允许根据涡轮喷气发动机的节气门设置来调节进入具有较大直径开口的扇区的空气。
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公开(公告)号：US5339622A
公开(公告)日：1994-08-23
申请号：US107175
申请日：1993-08-17
申请人： Xavier M. H. Bardey , Michel A. A. Desaulty , Jerome E. R. Jolu , Serge M. Meunier , Pierre C. Mouton , Sylvie Poutonnet , Jacques Renvier
发明人： Xavier M. H. Bardey , Michel A. A. Desaulty , Jerome E. R. Jolu , Serge M. Meunier , Pierre C. Mouton , Sylvie Poutonnet , Jacques Renvier
CPC分类号： F01D25/32 , F04D29/701 , F23R3/04 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine is disclosed having an air compressor and a generally annular combustion chamber, with a generally annular diffuser located between the compressor and the combustion chamber so as to direct air exiting from the compressor toward the combustion chamber. The diffuser has inner and outer walls and defines an exit which is located adjacent to an opening in an upstream wall portion of the combustion forming a dome cowl. The dome cowl divides the air emanating from the diffuser exit into a primary air stream passing through the opening and one or more secondary air streams which pass between the walls defining the combustion chamber and the walls of a casing enclosing the combustion chamber assembly. A guide is associated with the diffuser for directing water in the air passing through the diffuser away from the opening such that it will not pass directly into the combustion chamber. Guide vanes may be located on an external surface of the dome cowl so as to direct the water in the secondary air-flow such that it does not enter openings defined by the outer combustion chamber wall, thereby preventing the water from entering the combustion chamber.
摘要翻译： 公开了一种燃气涡轮发动机，其具有空气压缩机和大体上环形的燃烧室，其具有位于压缩机和燃烧室之间的大致环形的扩散器，以便将从压缩机排出的空气引向燃烧室。 扩散器具有内壁和外壁，并且限定出口，其邻近于形成圆顶罩的燃烧的上游壁部分中的开口定位。 圆顶罩将从扩散器出口排出的空气分隔成通过开口的一次空气流和在限定燃烧室的壁和封闭燃烧室组件的壳体的壁之间通过的一个或多个二次空气流。 引导件与扩散器相关联，用于将通过扩散器的空气中的水引导离开开口，使得其不会直接通过燃烧室。 引导叶片可以位于圆顶罩的外表面上，以便引导二次空气流中的水，使得其不会进入由外部燃烧室壁限定的开口，从而防止水进入燃烧室。
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公开(公告)号：US5295354A
公开(公告)日：1994-03-22
申请号：US834820
申请日：1992-02-13
CPC分类号： F23R3/34 , F23R3/04 , F23R3/54 , Y02T50/675
摘要： A low pollution combustion chamber for a turbojet engine is disclosed in which first and second combustion chambers are oriented in a counter-flow direction and both combustion chambers communicate with a separate and distinct exhaust chamber. The first combustion chamber has a fuel injector, as well as a primary oxidizer intake, and the wall bounding the first combustion chamber defines a plurality of dilution oxidizer intake orifices. The wall also defines a first exhaust orifice located approximately midway between the upstream and downstream ends of the first combustion chamber. A second combustion chamber has a second fuel injector, as well as a second primary oxidizer intake, but the wall defining the second combustion chamber does not define any dilution oxidizer intake orifices. A second exhaust orifice also communicates with the exhaust chamber. The orientations of the first and second combustion chambers are such that the fuel/oxidizer mixtures traveling through the combustion chambers travel in a generally counterflow arrangement. A separate exhaust chamber is included in the combustion chamber assembly and communicates with the first and second combustion chambers such that the burned gases from these chambers enter the exhaust chamber. The exhaust chamber defines a third exhaust orifice through which the burned gases exit the combustion chamber assembly. The exhaust chamber is oriented such that the exhaust gases passing through this exhaust chamber travel in a direction generally parallel to the gases traveling through the second combustion chamber. A wall defining the combustion chamber defines a second plurality of dilution oxidizer intake orifices so that oxidizer may dilute the exhaust gases passing through this chamber.
摘要翻译： 公开了一种用于涡轮喷气发动机的低污染燃烧室，其中第一和第二燃烧室在逆流方向上定向，并且两个燃烧室与单独且不同的排气室连通。 第一燃烧室具有燃料喷射器以及初级氧化剂入口，并且与第一燃烧室相邻的壁限定多个稀释氧化剂吸入口。 壁还限定位于第一燃烧室的上游和下游端之间大约中间的第一排气孔。 第二燃烧室具有第二燃料喷射器以及第二主要氧化剂入口，但限定第二燃烧室的壁不限定任何稀释氧化剂吸入口。 第二排气口还与排气室连通。 第一和第二燃烧室的取向使得通过燃烧室运行的燃料/氧化剂混合物以大致逆流排列行进。 在燃烧室组件中包括单独的排气室，并与第一和第二燃烧室连通，使得来自这些室的燃烧气体进入排气室。 排气室限定第三排气孔，燃烧的气体通过该第三排气孔离开燃烧室组件。 排气室被定向为使得通过该排气室的废气沿大致平行于穿过第二燃烧室的气体的方向行进。 限定燃烧室的壁限定第二多个稀释氧化剂吸入孔，使得氧化剂可以稀释通过该室的废气。
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公开(公告)号：US5211675A
公开(公告)日：1993-05-18
申请号：US822754
申请日：1992-01-21
摘要： A variable volume combustion chamber for a gas turbine engine that has a able wall to vary the volume of the combustion chamber. The movable wall is positioned according to the operating conditions of the gas turbine engine, achieving one extreme position under idle power and another extreme position under full power. The movement of the wall between the two extreme positions maximizes the efficiency of the combustion chamber for operating conditions between idle and full power. The combustion chamber also restricts at least a portion of the oxidizer intake when the movable wall is positioned for idle power conditions and opens the oxidizer intake when the wall is positioned for maximum power conditions to maximize the flow of oxidizer into the combustion chamber.
摘要翻译： 一种用于燃气涡轮发动机的可变容积燃烧室，其具有可改变燃烧室容积的可移动壁。 可动壁根据燃气涡轮发动机的运行条件定位，在空载功率下达到一个极限位置，在全功率下达到另一极限位置。 在两个极端位置之间的壁的运动使燃烧室的效率最大化，以在空转和全功率之间操作条件。 当可移动壁定位用于空闲功率条件时，燃烧室还限制至少一部分氧化剂吸入口，并且当壁被定位用于最大功率条件时打开氧化剂吸入口，以使氧化剂进入燃烧室的流动最大化。
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9.发明授权Gas turbine combustion chamber wall structure for minimizing cooling film disturbances 失效用于最小化冷却膜的气体涡轮机燃烧室壁结构
公开(公告)号：US5209067A
公开(公告)日：1993-05-11
申请号：US778283
申请日：1991-10-17
申请人： Gerard Y. G. Barbier , Frederic; B. Beule , Michel A. A. Desaulty , Jean M. C. M. P. Latour , Bruno R. H. Masse
发明人： Gerard Y. G. Barbier , Frederic; B. Beule , Michel A. A. Desaulty , Jean M. C. M. P. Latour , Bruno R. H. Masse
CPC分类号： F23R3/06 , F23R3/08 , Y02T50/675
摘要： A combustion chamber wall structure is formed of a plurality of segments, each segment having an upstream portion and a downstream portion. The upstream portion is attached to an outer surface of an adjacent wall segment at its downstream portion in an overlapping fashion such that the overlapping portions form a cooling air chamber. The main cooling air holes are defined by the upstream portion so as to communicate with the cooling chamber, which has an exit to direct the cooling air along an inner surface of the downstream portion of the wall segment. A primary air hole is defined by the downstream portion of the segment and is located adjacent to the main cooling air holes. This location maximizes the distance between the primary air hole and an upstream portion of the same segment, which, in turn, maximizes the distance along the inner surface of the segment on which the cooling air may flow without being disrupted by air passing through the primary air hole. The guidance of the primary/dilution air streams can also be carried out by a portion of the downstream air cooling film.
摘要翻译： 燃烧室壁结构由多个段形成，每个段具有上游部分和下游部分。 上游部分以其重叠的方式在其下游部分处附接到相邻壁段的外表面，使得重叠部分形成冷却空气室。 主冷却空气孔由上游部分限定，以便与具有出口的冷却室连通，以沿着壁段的下游部分的内表面引导冷却空气。 一个主要空气孔由该段的下游部分限定，并且位于主冷却空气孔附近。 该位置使得主空气孔和同一段的上游部分之间的距离最大化，这又使得沿着冷却空气可流动的段的内表面的距离最大化，而不会被穿过主要空气的空气中断 气孔。 初级/稀释气流的引导也可以由下游空气冷却膜的一部分进行。
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公开(公告)号：US5335491A
公开(公告)日：1994-08-09
申请号：US118249
申请日：1993-09-09
摘要： A generally annular combustion chamber for a gas turbine engine is disclosed in which a plurality of generally cylindrical walls extend forwardly from an upstream end wall of the combustion chamber such that each cylindrical wall defines a cavity which is in communication with the interior of the combustion chamber. A first fuel injection head is located in each of the cylindrical walls so as to inject fuel into the cavity which is mixed with air and passes into the combustion chamber. The first fuel injection heads are located at a first axial position with respect to a longitudinal axis passing through the combustion chamber. A plurality of second fuel injection heads are located adjacent to the upstream end wall of the combustion chamber so as to spray fuel directly into the combustion chamber. The second fuel injection heads are located axially downstream of the axial positions of the first fuel injection heads.
摘要翻译： 公开了一种用于燃气涡轮发动机的大体上环形的燃烧室，其中多个大致圆柱形的壁从燃烧室的上游端壁向前延伸，使得每个圆柱形壁限定了与燃烧室内部连通的空腔 。 第一燃料喷射头位于每个圆柱形壁中，以将燃料喷射到与空气混合并进入燃烧室的空腔中。 第一燃料喷射头位于相对于穿过燃烧室的纵向轴线的第一轴向位置。 多个第二燃料喷射头位于燃烧室的上游端壁附近，以将燃料直接喷入燃烧室。 第二燃料喷射头位于轴向位于第一燃料喷射头的轴向位置的下游。
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