公开(公告)号：US20140230404A1

公开(公告)日：2014-08-21

申请号：US14263098

申请日：2014-04-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Guy LEFEBVRE ,  Nicolas GRIVAS ,  Richard BOUCHARD ,  Denis LECLAIR ,  Eric DUROCHER

IPC: F02K1/38

CPC classification number: F02K1/386 ,  F01D9/04 ,  F02K1/48 ,  F02K1/80 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/10 ,  F05D2240/127 ,  Y02T50/671

Abstract: An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.

Abstract translation: 用于燃气涡轮发动机的排气混合器包括具有适于紧固到发动机壳体的上游端的环形壁和形成多个内部和外部混合器凸角的下游端。 支撑构件互连至少多个内裂片，并且包括从内裂片径向向内定位的周向延伸的加强环，以及一系列周向间隔开的从内裂纹到加强环径向延伸的混合器支柱。 混合器支柱具有至少等于限定在内部叶片和排气锥体之间的主气体通道的宽度的径向长度，使得混合器支柱完全延伸穿过主气体路径。 加强环仅被固定到混合器支柱上，以便相对于排气锥体浮动并允许它们之间的相对运动。

公开(公告)号：US20140165533A1

公开(公告)日：2014-06-19

申请号：US13717898

申请日：2012-12-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andreas ELEFTHERIOU ,  Denis LECLAIR ,  David DENIS ,  David MENHEERE ,  Paul AITCHISON

IPC: F02K3/04

CPC classification number: F01D25/162 ,  F02K3/06 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/4932

Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.

Abstract translation: 一种用于飞行器发动机的壳体包括外圈和限定其间的气流通道的内毂，所述外圈具有限定轴向的轴线; 多个支柱，其布置成周向阵列并且从所述内毂径向延伸到所述外环以将所述内毂安装到所述外环; 其中所述外环由双层皮肤限定，所述双层皮肤包括与所述金属板的环形内表面同心地围绕并径向间隔开的轴向延伸的环形外皮，所述外表皮和内表皮大体上彼此平行， 端环和环形后端环，其与外表面和内表面相邻地焊接或钎焊，所述外表面和内表面邻近表皮的前后边缘以在其间限定环形空腔，并且所述外环还包括多个周向间隔开的轴向延伸的肋， 外皮和内皮加固双面皮。