专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

81. 发明申请

WO2014137443A2 GAS TURBINE ENGINE TURBINE BLADE TIP COOLING 审中-公开
标题翻译：燃气涡轮发动机涡轮叶片头部冷却
公开(公告)号：WO2014137443A2
公开(公告)日：2014-09-12
申请号：PCT/US2013/075796
申请日：2013-12-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： AUXIER, James T. , O'HEARN, Jason L. , SLAVENS, Thomas N. , GIRMA, Yafet
CPC分类号： F01D5/186 , F01D5/20 , F01D11/08 , F05D2240/307 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.
摘要翻译：用于燃气涡轮发动机的翼型件包括彼此间隔开并且在前缘和后缘处连接的压力壁和吸入壁，以提供具有沿径向方向延伸至尖端的外表面的翼型件。尖端处的弧线从前缘延伸至后缘。压力和吸力侧架分别布置在弯曲线的相对侧上的外表面中的压力和吸力侧壁中。一个高原是自豪的和分离的压力和吸入侧货架。高原沿弧线排列并延伸到前缘。

82. 发明申请

WO2014133938A1 GAS TURBINE ENGINE STATOR VANE PLATFORM REINFORCEMENT 审中-公开
标题翻译：气体涡轮发动机定子叶片平台加固
公开(公告)号：WO2014133938A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/017927
申请日：2014-02-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KASTEL, Donald
IPC分类号： F01D17/16 , F02C9/20
CPC分类号： F01D9/04 , F01D5/147 , F01D9/041 , F01D25/246 , F02C3/04 , F05D2240/125 , F05D2240/80 , F05D2250/60
摘要： A stator vane for a gas turbine engine includes a first platform and a second platform radially spaced apart from one another. The first and second airfoils are circumferentially spaced from one another and interconnect the first and second platforms. The first platform has a gas path side facing the airfoils and a non-gas path side opposite the gas path side. A circumferentially extending rail provided on the first platform extends radially outward from the gas path side to the non-gas path side to form a pocket on the non-gas path side between the first platform and the rail. A reinforcement is arranged in the pocket and joins the first platform and the rail. The reinforcement includes a variable thickness in the circumferential direction and is arranged generally centrally between the first and second airfoils.
摘要翻译：用于燃气涡轮发动机的定子叶片包括第一平台和彼此径向间隔开的第二平台。第一和第二翼型件彼此周向间隔开并且互连第一和第二平台。第一平台具有面向翼型的气体路径侧和与气体路径侧相对的非气体通路侧。设置在第一平台上的周向延伸的轨道从气体路径侧径向向外延伸到非气体路径侧，以在第一平台和轨道之间的非气体路径侧上形成口袋。口袋中布置有一个加强件，并且连接在第一平台和导轨上。加强件在圆周方向上包括可变的厚度，并且大体中心布置在第一和第二翼型之间。

83. 发明申请

WO2014133770A1 GAS TURBINE ENGINE NOISE REDUCING NOSE CONE 审中-公开
标题翻译：气体涡轮发动机噪音减少噪声
公开(公告)号：WO2014133770A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/016196
申请日：2014-02-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GILSON, Jonathan , SAWYERS-ABBOTT, Nigel David
IPC分类号： F02C7/045 , F02C7/04 , F01D25/00
CPC分类号： F02C7/045 , F01D5/02 , F01D25/24 , F05D2220/32 , F05D2220/36 , F05D2260/963
摘要： A fan section for a gas turbine engine includes a fan hub and a nose cone section operatively mounted to the fan hub. The nose cone section includes a noise attenuation feature.
摘要翻译：用于燃气涡轮发动机的风扇部分包括可操作地安装到风扇轮毂的风扇轮毂和鼻锥部分。鼻锥部分包括噪声衰减特征。

84. 发明申请

WO2014130245A1 DIE CONFIGURATION FOR HIGH TEMPERATURE DIECASTING 审中-公开
标题翻译：用于高温预处理的DIE配置
公开(公告)号：WO2014130245A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/014900
申请日：2014-02-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BULLIED, Steven J. , PANDEY, Awadh B. , TRYON, Brian S.
IPC分类号： B22D17/22
CPC分类号： B22D17/2209 , B22D17/229
摘要： A die casting die includes a shoe comprised of a first material and includes a pocket. An insert is arranged in the pocket. The insert is comprised of a second material that is different from the first material and the insert provides a contoured surface. A coating is on the contoured surface. The coating provides a cast part contour.
摘要翻译：压铸模具包括由第一材料构成并包括袋的鞋。插入物被布置在口袋中。插入件由与第一材料不同的第二材料组成，并且插入件提供轮廓表面。涂层在轮廓表面上。涂层提供铸件轮廓。

85. 发明申请

WO2014105236A2 AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT 审中-公开
标题翻译：带可变行程杆高度的AIRFOIL
公开(公告)号：WO2014105236A2
公开(公告)日：2014-07-03
申请号：PCT/US2013/061857
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORPORATION , RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
发明人： RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
CPC分类号： F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
摘要： An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
摘要翻译：用于燃气涡轮发动机的翼型件组件包括从平台延伸的翼型件。翼型件和平台中的至少一个包括由表面限定的冷却通道。人字形跳闸条从表面延伸到沿着长度的跳闸条高度处的冷却通路。跳闸条高度沿长度变化。用于燃气涡轮发动机的涡轮叶片包括内部和外部平台。内部平台上设有冷却通道。冷却通道由第一和第二径向延伸的腿部提供，所述第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接。一对翼型从相同的内部平台径向延伸。跳闸条从表面沿着长度以跳闸条高度从表面延伸到圆周通道中。跳闸高度沿长度变化。

86. 发明申请

WO2014058493A2 SUCTION SIDE TURBINE BLADE TIP COOLING 审中-公开
标题翻译：吸气侧涡轮叶片头部冷却
公开(公告)号：WO2014058493A2
公开(公告)日：2014-04-17
申请号：PCT/US2013/050429
申请日：2013-07-15
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CHLUS, Wieslaw A. , THOMEN, Seth J.
IPC分类号： F01D5/18 , F02C7/12
CPC分类号： F01D5/20 , F05D2250/14 , F05D2250/232 , F05D2250/324 , F05D2260/202 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.
摘要翻译：用于燃气涡轮发动机的翼型件包括彼此间隔开并且在前缘和后缘处连接以提供沿径向方向延伸的翼型件的压力壁和吸入壁。翼型具有布置在朝向翼型的尖端延伸的压力壁和抽吸壁之间的冷却通道。尖端包括一个将压力和吸力壁分开的凹槽。带棱纹的冷却孔将冷却通道流体连接到口袋。有棱角的冷却孔包括一部分凹入吸入壁面并暴露在口袋中。

87. 发明申请

WO2014046735A1 FAN BLADE TALL DOVETAIL FOR INDIVIDUALLY BLADED ROTORS 审中-公开
标题翻译：风扇叶片，适用于独立的叶片转子
公开(公告)号：WO2014046735A1
公开(公告)日：2014-03-27
申请号：PCT/US2013/031868
申请日：2013-03-15
申请人： UNITED TECHNOLOGIES CORPORATION , WHITEHURST, Sean A. , MCCOMB, Patrick James , DROZDENKO, Lee
发明人： WHITEHURST, Sean A. , MCCOMB, Patrick James , DROZDENKO, Lee
IPC分类号： F01D5/30 , F02C7/00
CPC分类号： F01D5/303 , F01D5/28 , F01D5/3007 , F01D5/3092 , F02C3/04 , F05D2220/36 , F05D2250/70 , F05D2270/114 , Y02T50/671
摘要： A fan blade for a gas turbine engine includes an airfoil that defines a pressure and suction side. A neck supports the airfoil and interconnects to a dovetail by opposing radii. The dovetail includes a bearing surface tangent to one of the radii at a tangent point. The dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck. A first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90.
摘要翻译：用于燃气涡轮发动机的风扇叶片包括限定压力和吸力侧的翼型件。颈部支撑翼型，并通过相对的半径与燕尾互连。燕尾包括在切点处与半径中的一个相切的支承表面。燕尾榫具有燕尾宽度和垂直轴承表面高度，从切线点到燕尾榫的与颈部相对的底部。燕尾宽度与垂直承载面高度的第一比率在2.32至2.90之间的范围内。

88. 发明申请

WO2014042956A1 TURBINE AIRFOIL PLATFORM RAIL WITH GUSSET 审中-公开
标题翻译：涡轮机空气平台铁路与GUSSET
公开(公告)号：WO2014042956A1
公开(公告)日：2014-03-20
申请号：PCT/US2013/058289
申请日：2013-09-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： THOMEN, Seth, J. , PIETRASZKIEWICZ, Edward, F.
IPC分类号： F01D5/14 , F01D5/00 , F02C7/00 , F02K3/00
CPC分类号： F01D5/147 , F01D5/3007 , F05D2240/80
摘要： A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank.
摘要翻译：用于燃气涡轮发动机的叶片包括连接根部和平台的杆以及从柄径向延伸的翼型件。柄包括一个口袋，该口袋具有悬挂在口袋上的平台。轨道沿着平台的侧边缘轴向延伸并且沿着与翼型相反的方向从平台径向向内延伸。角撑板从平台的面向腔体的下侧延伸并且在轨道和柄之间的圆周方向上延伸。

89. 发明申请

WO2014039198A1 FAN CASE BALLISTIC LINER AND METHOD OF MANUFACTURING SAME 审中-公开
标题翻译：风扇式弹簧衬板及其制造方法
公开(公告)号：WO2014039198A1
公开(公告)日：2014-03-13
申请号：PCT/US2013/053893
申请日：2013-08-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： CLARKSON, Steven
IPC分类号： B21D51/18 , B21D41/02 , B21D39/08
CPC分类号： F01D21/045 , B29C53/562 , B29C63/34 , F01D25/24 , F02C7/045 , F02C7/057 , F02K1/827 , Y02T50/672
摘要： A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.
摘要翻译：制造具有衬垫的风扇壳体的方法包括以下步骤：提供具有切割和第一直径的圆形横截面的预成型件，使预成型件弯曲以将第一直径减小到第二直径，并将预成型件粘合到风扇外壳的内表面。燃气轮机的风扇壳体具有内表面的风扇壳体。预制件粘附到内表面并具有提供间隙的切口。

90. 发明申请

WO2014022065A1 ANTI-ROTATION LUG FOR A GAS TURBINE ENGINE STATOR ASSEMBLY 审中-公开
标题翻译：用于气体涡轮发动机定子组件的反转油
公开(公告)号：WO2014022065A1
公开(公告)日：2014-02-06
申请号：PCT/US2013/049855
申请日：2013-07-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： TATMAN, Neil L. , HAYFORD, Richard K.
IPC分类号： F02C7/00 , F02C7/32 , F02C9/00 , F01D9/00
CPC分类号： F01D9/042 , F01D11/08 , F01D25/246 , F05D2240/11 , F05D2260/30 , Y10T29/49245 , Y10T74/20636
摘要： A stator assembly includes a case including an arcuate wall having an aperture with circumferentially spaced first lateral surfaces. A stator vane has an outer platform with a notch. An anti-rotation lug has a base that is received in the notch and a boss extends from the base. The boss is received in the aperture. The boss has second lateral surfaces that engage the first lateral surfaces in an interference fit relationship.
摘要翻译：定子组件包括壳体，该壳体包括具有带圆周间隔开的第一侧面的孔的弧形壁。定子叶片具有带有凹口的外平台。防旋转凸耳具有容纳在凹口中的基部，并且凸起从基部延伸。老板被接收在光圈中。凸台具有以干涉配合关系与第一侧表面接合的第二侧表面。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式