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公开(公告)号：JP2013108500A
公开(公告)日：2013-06-06
申请号：JP2012255781
申请日：2012-11-22
Inventor： DAVIS TODD A , REINHARDT GREGORY E , DIBENEDETTO ENZO
CPC classification number: F02K3/06 , F01D25/164 , F02C3/107 , Y02T50/671
Abstract: PROBLEM TO BE SOLVED: To configure a case structure of an engine to mitigate displacement of a position relation of gear components.SOLUTION: An engine 10 includes: a case structure 160; an intermediate case structure 162; a low pressure compressor 144; first, second, third bearing system 138-1, 138-2, 138-3; and a low pressure compressor hub 184. The bearing system 138-2 is attached to the case structure 160 to support an inner shaft 140, and the bearing system 138-3 is attached to the intermediate case structure 162 to support an outer shaft 150. The low pressure compressor hub 184 is attached to the inner shaft 140 between the bearing system 138-2, 3 to extend toward the low pressure compressor 144. A gear device 148 is attached to the bearing system 138-2 via a coupling shaft 174. The low pressure compressor hub 184 is arranged between the bearing system 138-2, 3 such that deformation of the gear device 148 is reduced.
Abstract translation: 要解决的问题：构造发动机的壳体结构以减轻齿轮部件的位置关系的位移。 发动机10包括：壳体结构160; 中间壳体结构162; 低压压缩机144; 第一，第二，第三轴承系统138-1,138-2,138-3; 和低压压缩机毂184.轴承系统138-2附接到壳体结构160以支撑内轴140，并且轴承系统138-3附接到中间壳体结构162以支撑外轴150。 低压压缩机毂184附接到轴承系统138-2,3之间的内轴140，以朝向低压压缩机144延伸。齿轮装置148通过联接轴174附接到轴承系统138-2。 低压压缩机毂184布置在轴承系统138-2,3之间，使齿轮装置148的变形减小。 版权所有（C）2013，JPO＆INPIT
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公开(公告)号：WO2013147969A3
公开(公告)日：2013-12-27
申请号：PCT/US2013020466
申请日：2013-01-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MULDOON MARC J , REINHARDT GREGORY E
CPC classification number: F02C7/06 , F01D11/005 , F01D11/02 , F01D11/04 , F01D25/16 , F01D25/183 , F01D25/20 , F01D25/28 , F02C3/10 , F02C6/08 , F02C7/20 , F02C7/28 , F02K3/06 , F05D2220/36 , F05D2240/56 , F05D2260/98 , F05D2300/224 , F16J15/40
Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.
Abstract translation: 用于燃气涡轮发动机的中间涡轮机框架缓冲系统包括通过轴承支撑轴的中间涡轮机框架。 空气室和轴承室布置在中间涡轮机框架的径向内侧。 轴承室布置在空气室内并且包括布置在轴承两侧的第一和第二接触密封件。 空气室包括多个空气密封。 高压压缩机流体连接到空气室，并构造成向空气室提供高压空气。 一种向缓冲系统提供加压空气的方法包括用接触密封件密封轴承室，用空气室围绕轴承室，并向空气室提供高压空气。
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公开(公告)号：DE60221074T2
公开(公告)日：2008-03-13
申请号：DE60221074
申请日：2002-05-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , MERRY BRIAN , DOLANSKY GREGORY M , REINHARDT GREGORY E
Abstract: The present invention relates to a method for repairing a turbine blade 10 having a crack 16 in a trailing edge portion 26 of the blade 10. The disclosed method comprises the steps of cutting back a first surface 18 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located, and cutting back a second surface 20 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located. Each cut back step comprises cutting back the respective surface 18,20 by a depth L greater than the length of the crack 16 and less than the trailing edge radius to remove the crack 16 and form a cut back trailing edge portion 28. A compound radius is used to prevent a blunt transition into the trailing edge 12 that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade 10 to increase service life. Prior to applying the coating, the tip portion 46 of the turbine blade 10 is modified to account for the change in the thermal characteristics of the turbine blade 10.
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公开(公告)号：BR102012027097A2
公开(公告)日：2013-11-05
申请号：BR102012027097
申请日：2012-10-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DAVIS TODD A , REINHARDT GREGORY E , DIBENEDETTO ENZO
IPC: F02K3/00
Abstract: A method for servicing a gas turbine engine (120) includes providing access from a forward section of the gas turbine engine (120) to a gearbox (148) contained within a bearing compartment (B).
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公开(公告)号：CA2881861C
公开(公告)日：2019-08-20
申请号：CA2881861
申请日：2013-09-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MAJOR DANIEL W , REINHARDT GREGORY E , REMBISH PAUL THOMAS , SPAULDING BARRY WILLIAM , SUMMERS DONALD
Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.
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Patent Agency Ranking
公开(公告)号：CA2881861A1
公开(公告)日：2014-03-27
申请号：CA2881861
申请日：2013-09-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MAJOR DANIEL W , REINHARDT GREGORY E , REMBISH PAUL THOMAS , SPAULDING BARRY WILLIAM , SUMMERS DONALD
Abstract: A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.
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公开(公告)号：CA2794888A1
公开(公告)日：2013-05-23
申请号：CA2794888
申请日：2012-11-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DAVIS TODD A , REINHARDT GREGORY E , DIBENEDETTO ENZO
Abstract: A method for servicing a gas turbine engine includes providing access from a forward section of the gas turbine engine to a gearbox contained within a bearing compartment.
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公开(公告)号：DE60221074D1
公开(公告)日：2007-08-23
申请号：DE60221074
申请日：2002-05-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SURACE RAYMOND C , MERRY BRIAN , DOLANSKY GREGORY M , REINHARDT GREGORY E
Abstract: The present invention relates to a method for repairing a turbine blade 10 having a crack 16 in a trailing edge portion 26 of the blade 10. The disclosed method comprises the steps of cutting back a first surface 18 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located, and cutting back a second surface 20 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located. Each cut back step comprises cutting back the respective surface 18,20 by a depth L greater than the length of the crack 16 and less than the trailing edge radius to remove the crack 16 and form a cut back trailing edge portion 28. A compound radius is used to prevent a blunt transition into the trailing edge 12 that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade 10 to increase service life. Prior to applying the coating, the tip portion 46 of the turbine blade 10 is modified to account for the change in the thermal characteristics of the turbine blade 10.
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公开(公告)号：CA2564073A1
公开(公告)日：2007-04-27
申请号：CA2564073
申请日：2006-10-13
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ALVANOS IOANNIS , AGRAWAL RAJENDRA , REINHARDT GREGORY E
Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
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公开(公告)号：CA2945459A1
公开(公告)日：2017-04-15
申请号：CA2945459
申请日：2016-10-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MURPHY GABRIELLE , LEWIS ROBERT M , REINHARDT GREGORY E
Abstract: A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module.
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