公开(公告)号：WO2012118516A8

公开(公告)日：2012-09-07

申请号：PCT/US2011/036630

申请日：2011-05-16

Applicant: GENERAL ELECTRIC COMPANY ,  MILLARD, Michael, Lee ,  MEIBERS, Gregory, Joseph ,  HALL, Kathleen, Raftery ,  RENGGLI, Bernard, James ,  MILLER, Jeffrey, Franklin

Inventor： MILLARD, Michael, Lee ,  MEIBERS, Gregory, Joseph ,  HALL, Kathleen, Raftery ,  RENGGLI, Bernard, James ,  MILLER, Jeffrey, Franklin

IPC: B32B18/00 ,  C04B35/565 ,  C04B35/80 ,  C04B35/82 ,  C04B37/00 ,  C04B35/626 ,  B64D33/04

Abstract: Ceramic matrix composite sandwich structures, gas turbine engine components that comprise such sandwich structures, and methods of producing such sandwich structures. The ceramic matrix composite sandwich structure includes a core having oppositely-disposed first and second surfaces, a first facesheet bonded to the first surface, and a member bonded to the second surface so that the core is between the first facesheet and the member. The first facesheet and the core comprise, respectively, first and second ceramic matrix composite materials, and the second ceramic matrix composite material of the core has a ceramic reinforcement material in the form of a felt or an open weave fabric.

公开(公告)号：WO2014058502A2

公开(公告)日：2014-04-17

申请号：PCT/US2013/051201

申请日：2013-07-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： RENGGLI, Bernard, James ,  MILLER, Jeffrey, Franklin

IPC: B32B18/00

CPC classification number: F01D25/005 ,  B32B18/00 ,  C04B35/18 ,  C04B35/803 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5268 ,  C04B2237/341 ,  C04B2237/38 ,  F01D25/24 ,  F02C3/10 ,  F02C7/20 ,  F02K1/04 ,  F05D2300/6033 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T29/4932

Abstract: A ceramic centerbody (120) for an aircraft gas turbine engine. The ceramic centerbody (120) comprises an interlaced fiber structure having fibers oriented in a substantially transverse directions and a ceramic matrix surrounding the ceramic fiber structure. The ceramic fiber and matrix are formed into a conical shape having a fore end (128) and an aft end (126). The centerbody includes a means for mechanical attachment (130) circumferentially oriented around the fore end of the centerbody. The fore end further includes additional plies oriented in a third preselected direction, thereby providing additional strength to for mechanical attachment.

Abstract translation: 一种用于飞机燃气涡轮发动机的陶瓷中心体（120）。 陶瓷中心体（120）包括具有基本横向取向的纤维的交织纤维结构和围绕陶瓷纤维结构的陶瓷基体。 陶瓷纤维和基体形成为具有前端（128）和后端（126）的圆锥形状。 中心体包括围绕中心体的前端周向定向的机械附接装置（130）。 前端还包括以第三预选方向定向的附加层，从而为机械附接提供额外的强度。

公开(公告)号：WO2014022344A1

公开(公告)日：2014-02-06

申请号：PCT/US2013/052630

申请日：2013-07-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： RENGGLI, Bernard, James ,  KEY, Caroline, Elizabeth ,  LAUDE, Anthony

IPC: F02K1/78 ,  B64D29/00 ,  C04B35/645 ,  F02K3/06

CPC classification number: F01D25/005 ,  C04B35/18 ,  C04B35/565 ,  C04B35/803 ,  C04B35/806 ,  C04B2235/5224 ,  C04B2235/5244 ,  C04B2235/5268 ,  C04B2235/94 ,  F02K1/78 ,  F02K3/06 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A CMC core cowl (120) for an aircraft gas turbine engine (10). The ceramic core cowl comprises an interlaced fiber structure having fibers oriented in substantially transverse directions, and a ceramic matrix surrounding the ceramic fiber structure. The core cowl further comprises several panels (150, 152, 154, 156). The ceramic fiber and matrix are formed into a substantially cylindrical shape extending from a fore end at the fan outlet guide vanes to an aft end at the low pressure turbine outlet guide vanes. The CMC core cowl (120) includes a means for mechanical attachment (170) circumferentially oriented around the fore end and the aft end with mating parts. The CMC core cowl further includes additional plies oriented in a third preselected direction, thereby providing additional strength for mechanical attachment.

Abstract translation: 一种用于飞机燃气涡轮发动机（10）的CMC核心罩（120）。 陶瓷芯罩包括具有基本横向取向的纤维的交织纤维结构和围绕陶瓷纤维结构的陶瓷基体。 芯套还包括几个面板（150,152,154,156）。 陶瓷纤维和基体形成为从风扇出口导叶的前端延伸到低压涡轮机出口导向叶片的后端的大致圆柱形。 CMC核心罩（120）包括用于机械附接（170）的装置，其围绕前端和后端具有配合部分周向定向。 CMC核心外罩还包括以第三预选方向定向的附加层，从而为机械附接提供额外的强度。

公开(公告)号：WO2013163510A1

公开(公告)日：2013-10-31

申请号：PCT/US2013/038352

申请日：2013-04-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： RUTHEMEYER, Michael, Anthony ,  SENILE, Darrell, Glenn ,  RENGGLI, Bernard, James ,  LEWIS, Randy, Lee

IPC: F02K1/04 ,  F02K1/80

CPC classification number: F02C7/20 ,  F02K1/04 ,  F02K1/48 ,  F02K1/80 ,  F23R3/007 ,  Y02T50/672

Abstract: A gas turbine engine assembly includes first and second annular members (41, 48) having different first and second thermal expansion coefficients that are connected together with dual arm V brackets (50), where brackets (50) include first and second arms (62, 64) angularly spaced apart from a bracket centerline (70) and extending axially away from bracket bases (72) attached to a first one of the first and second annular members (41, 48), and arms (62, 64) are attached to a second one of the first and second annular members (41, 48).

Abstract translation: 燃气涡轮发动机组件包括具有不同的第一和第二热膨胀系数的第一和第二环形构件（41,48），其与双臂V支架（50）连接在一起，其中支架（50）包括第一和第二臂（62， 64），其与支架中心线（70）成角度地间隔开并且从附接到第一和第二环形构件（41,48）中的第一个的支架底座（72）轴向延伸并且臂（62,64）附接到 第一和第二环形构件（41,48）中的第二个。