公开(公告)号：WO2015023331A3

公开(公告)日：2015-04-09

申请号：PCT/US2014038723

申请日：2014-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  ALLEN RICHARD N ,  PORTER STEVEN D

IPC: F01D9/00 ,  F01D5/14 ,  F01D9/02

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D9/042 ,  F01D9/047 ,  F01D25/24 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/80 ,  Y02T50/673

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 用于燃气涡轮发动机的叶片具有在前缘和后缘之间延伸的翼型，并且通常是中空的。 叶片具有径向外部平台和径向内部平台。 径向内部和径向外部平台中的至少一个具有圆周地位于前缘和后缘中的一个之外的较厚部分以及周向地超过翼型件的周边边缘的较薄部分。 还公开了中间涡轮机框架和燃气涡轮发动机。

公开(公告)号：SG11201508706RA

公开(公告)日：2015-12-30

申请号：SG11201508706R

申请日：2014-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  ALLEN RICHARD N ,  PORTER STEVEN D

IPC: F01D5/14 ,  F01D9/00 ,  F01D9/02

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

公开(公告)号：EP3011141A4

公开(公告)日：2017-03-08

申请号：EP14813485

申请日：2014-05-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  ALLEN RICHARD N ,  PORTER STEVEN D ,  SANCHEZ PAUL K ,  PINERO SANDRA S

IPC: F01D9/02 ,  F01D5/02 ,  F01D5/14 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F01D9/04 ,  F01D9/047 ,  F01D25/24 ,  F05D2230/53 ,  Y02T50/671 ,  Y02T50/673

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 叶片具有在径向外平台和径向内平台之间延伸的翼型件。 至少一个平台具有标称径向较薄的部分，以及限定径向较厚部分的垫。 垫具有大于标称径向较薄部分的厚度的径向厚度。 衬垫在径向外平台的一侧围绕翼型件的外周。 垫具有变化的径向厚度。 还公开了中涡轮机架和燃气涡轮发动机。

公开(公告)号：EP3052764A4

公开(公告)日：2016-11-16

申请号：EP14850260

申请日：2014-09-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  ALLEN RICHARD N ,  PORTER STEVEN D ,  SANCHEZ PAUL K

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/80 ,  F05D2260/941 ,  Y02T50/671

公开(公告)号：EP3008291A4

公开(公告)日：2016-08-31

申请号：EP14836398

申请日：2014-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  ALLEN RICHARD N ,  PORTER STEVEN D

IPC: F01D9/00 ,  F01D5/14 ,  F01D9/02 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D9/042 ,  F01D9/047 ,  F01D25/24 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/80 ,  Y02T50/673

Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.

公开(公告)号：EP3022400A4

公开(公告)日：2016-07-20

申请号：EP14825846

申请日：2014-06-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： OLS JOHN T ,  MENTZ KARL A ,  ALLEN RICHARD N ,  PORTER STEVEN D ,  JUREK RENEE J ,  SANCHEZ PAUL K ,  PINERO SANDRA S

IPC: F01D9/04 ,  F01D5/02 ,  F01D5/14 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 翼型件在径向内部和径向外部平台之间延伸。 翼型件在前缘和后缘之间延伸，并且合并到径向内外平台的相对表面中。 可变圆角将径向内平台和外平台之一的面对面融合到翼型的壁中。 可变圆角具有远离翼型件的表面延伸的长度，并且从径向内部和外部平台中的至少一个的相对表面向外延伸到翼型的高度。 可变圆角在前缘和后缘之一处具有更大的长度。 间隔部分在与前缘和后缘中的至少一个间隔开的位置处具有较短的长度。 还公开了中涡轮机架和燃气涡轮发动机。