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公开(公告)号：US09651260B2
公开(公告)日：2017-05-16
申请号：US14344266
申请日：2012-09-20
Applicant: SNECMA
Inventor： Denis Jean Maurice Sandelis , Christophe Pieussergues
Abstract: An annular combustion chamber including inner and outer walls forming surfaces of revolution that are connected together upstream by an annular chamber end wall having injection systems passing therethrough. Each injection system includes at least one swirler for producing a rotating stream of air downstream from a fuel injector, and a frustoconical bowl downstream from the swirler and formed with an annular row of air injection orifices, the outer wall having an annular row of primary dilution orifices. The orifices of the bowls are distributed and dimensioned such that sheets of air/fuel mixture present a local enlargement circumferentially intersecting an adjacent sheet of fuel upstream from the primary dilution orifices.
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公开(公告)号：US20160084501A1
公开(公告)日：2016-03-24
申请号：US14708699
申请日：2015-05-11
Applicant: SNECMA
Inventor： Romain Nicolas LUNEL , Denis Jean Maurice Sandelis
CPC classification number: F23R3/002 , F01D25/243 , F01D25/265 , F01D25/28 , F23R3/44 , F23R3/50 , F23R3/60 , F23R2900/00005
Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.
Abstract translation: 一种涡轮发动机，其具有由两个同轴的环形护罩形成的环形燃烧室，相对于涡轮发动机的轴线的内护罩和外护罩，所述护罩一个在另一个内部并排设置，并且在其上游端通过环形 腔室端壁被紧固到围绕外部环形护罩的外壳上，内部和外部环形护罩的下游端分别连接到固定到内部壳体和外部壳体的凸缘。 内护罩和外护罩中的至少一个的上游端以径向抵靠环形室端壁的轴承为中心，并与其密封轴向滑动配合。
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公开(公告)号：US20150020501A1
公开(公告)日：2015-01-22
申请号：US14348966
申请日：2012-10-22
Applicant: SNECMA
Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.
Abstract translation: 涡轮发动机的环形燃烧室，所述腔室包括形成两个旋转表面的内部和外部同轴壁，其由包括通过其中的喷射系统的环形室端壁连接在一起，每个包括喷射器和至少一个旋流器， 产生将来自喷射器的燃料与下游混合的旋转空气流和安装在喷射系统下游的外壁的孔中的至少一个点火火花塞。 火花塞周向地位于两个相邻的喷射系统之间，其被配置为产生沿相反方向旋转的两个空气/燃料混合物片。
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Patent Agency Ranking
公开(公告)号：US09581334B2
公开(公告)日：2017-02-28
申请号：US14348966
申请日：2012-10-22
Applicant: SNECMA
Abstract: An annular combustion chamber of a turbine engine, the chamber including inner and outer coaxial walls forming two surfaces of revolution, which are connected together upstream by an annular chamber end wall including injection systems passing therethrough, each including an injector and at least one swirler for producing a rotating air stream that mixes downstream with fuel from the injector, and at least one ignition spark plug mounted in an orifice of the outer wall downstream from the injection systems. The spark plug is situated circumferentially between two adjacent injection systems that are configured to produce two air/fuel mixture sheets rotating in opposite directions.
Abstract translation: 涡轮发动机的环形燃烧室，所述腔室包括形成两个旋转表面的内部和外部同轴壁，其由包括通过其中的喷射系统的环形室端壁连接在一起，每个包括喷射器和至少一个旋流器， 产生将来自喷射器的燃料与下游混合的旋转空气流和安装在喷射系统下游的外壁的孔中的至少一个点火火花塞。 火花塞周向地位于两个相邻的喷射系统之间，其被配置为产生沿相反方向旋转的两个空气/燃料混合物片。
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公开(公告)号：US20150059344A1
公开(公告)日：2015-03-05
申请号：US14394214
申请日：2013-05-23
Applicant: SNECMA
Inventor： Denis Jean Maurice Sandelis
IPC: F23R3/06
CPC classification number: F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
Abstract: A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation.
Abstract translation: 涡轮机燃烧室壳环，其中涡轮机燃烧室壳环中的稀释孔用在壳环的内表面上限定相同腔室的插入物覆盖。 通过插入物的通风孔引起围绕稀释孔的壳环部分的通风，冷却部分，并防止裂纹形成。
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公开(公告)号：US10151485B2
公开(公告)日：2018-12-11
申请号：US14708699
申请日：2015-05-11
Applicant: SNECMA
Inventor： Romain Nicolas Lunel , Denis Jean Maurice Sandelis
Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.
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公开(公告)号：US09989256B2
公开(公告)日：2018-06-05
申请号：US14750347
申请日：2015-06-25
Applicant: SNECMA
Inventor： Denis Jean Maurice Sandelis , Romain Nicolas Lunel
CPC classification number: F23R3/14 , F02C7/22 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F23C7/004 , F23R3/286 , F23R3/343 , F23R3/36 , Y02T50/675
Abstract: An injection system for a turbine engine combustion chamber is provided. The injection system includes a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. The first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.
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公开(公告)号：US09377200B2
公开(公告)日：2016-06-28
申请号：US14394214
申请日：2013-05-23
Applicant: SNECMA
Inventor： Denis Jean Maurice Sandelis
CPC classification number: F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
Abstract: A turbomachine combustion chamber shell ring in which dilution holes in the turbomachine combustion chamber shell ring are covered with inserts defining chambers around same on an inner face of the shell ring. Ventilation holes, through the insert, induce ventilation of portions of the shell ring surrounding the dilution holes, cool the portions, and prevent crack formation.
Abstract translation: 涡轮机燃烧室壳环，其中涡轮机燃烧室壳环中的稀释孔用在壳环的内表面上限定相同腔室的插入物覆盖。 通过插入物的通风孔引起围绕稀释孔的壳环部分的通风，冷却部分，并防止裂纹形成。
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