公开(公告)号：EP2707589B1

公开(公告)日：2018-03-07

申请号：EP12728664.9

申请日：2012-05-11

申请人： Safran Aircraft Engines ,  Centre National de la Recherche Scientifique (C.N.R.S.) ,  Université De Poitiers ,  Ensma

发明人： VUILLEMIN, Alexandre, Alfred, Gaston ,  KOENIG, Maxime ,  JORDAN, Peter ,  GERVAIS, Yves

IPC分类号： F02K1/34 ,  F02K3/06

CPC分类号： F02K1/34 ,  F02K1/46 ,  F02K3/06 ,  F05D2250/411 ,  F05D2260/962 ,  Y02T50/671

公开(公告)号：EP2707589A1

公开(公告)日：2014-03-19

申请号：EP12728664.9

申请日：2012-05-11

申请人： Snecma ,  Centre National de la Recherche Scientifique (CNRS) ,  Université De Poitiers ,  Ensma

发明人： VUILLEMIN, Alexandre, Alfred, Gaston ,  KOENIG, Maxime ,  JORDAN, Peter ,  GERVAIS, Yves

IPC分类号： F02K1/34 ,  F02K3/06

CPC分类号： F02K1/34 ,  F02K1/46 ,  F02K3/06 ,  F05D2250/411 ,  F05D2260/962 ,  Y02T50/671

摘要： The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.

摘要翻译： 本发明涉及一种用于涡轮发动机的后壳体，其包括主体，其产生要通过主喷嘴（6）喷射的主流（10），所述后壳体（7）成形为位于主流体 并且在涡轮发动机的内侧上限定从主喷嘴（6）下游的主流的路径。 尾锥的特征在于，其包括与用于供应加压气体的系统的连接以及用于将加压气体通过穿孔注入主流的至少一个穿孔（8）。 壳体优选地包括至少一个用于围绕主体的可移动元件的旋转轴线旋转它的装置。

公开(公告)号：EP3274578B1

公开(公告)日：2019-05-01

申请号：EP16719444.8

申请日：2016-03-25

申请人： SAFRAN AIRCRAFT ENGINES

发明人： MARDJONO, Jacky ,  CHANEZ, Philippe ,  GONZALEZ, Jérémy ,  KOENIG, Maxime ,  VERSAEVEL, Marc ,  ZAGANELLI, Franck ,  YESILCIMEN, Henri

IPC分类号： F02K1/34 ,  F02K1/38

公开(公告)号：EP3274578A1

公开(公告)日：2018-01-31

申请号：EP16719444.8

申请日：2016-03-25

申请人： SAFRAN AIRCRAFT ENGINES

发明人： MARDJONO, Jacky ,  CHANEZ, Philippe ,  GONZALEZ, Jérémy ,  KOENIG, Maxime ,  VERSAEVEL, Marc ,  ZAGANELLI, Franck ,  YESILCIMEN, Henri

IPC分类号： F02K1/34 ,  F02K1/38

CPC分类号： F02K1/34 ,  F02K3/06 ,  F05D2220/323 ,  F05D2260/96 ,  F05D2270/306 ,  Y02T50/671

摘要： The invention relates to a device for reducing the jet noise of a turbine engine, comprising an outer cowl (16) provided inside a wall (20) defining on the outside an annular section (22) for the flow of a secondary stream from the turbine engine, said wall of the outer cowl comprising a plurality of microjet circuits (28) each comprising means (30) for sampling gas flows in the flow section of the secondary stream which open into a single supply pipe (32), which in turn opens onto a trailing edge of the outer cowl via at least one ejection grating (34) capable of dividing the sampled stream of gas into a plurality of streams of gas having cross-sections with dimensions smaller than a cross-section (
D ) of the supply pipe.