-
公开(公告)号：US11118481B2
公开(公告)日：2021-09-14
申请号：US15424930
申请日：2017-02-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
Abstract: A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.
-
公开(公告)号：US20190055888A1
公开(公告)日：2019-02-21
申请号：US16047634
申请日：2018-07-27
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
CPC classification number: F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
-
公开(公告)号：US10184402B2
公开(公告)日：2019-01-22
申请号：US15947890
申请日：2018-04-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.
-
公开(公告)号：US10138751B2
公开(公告)日：2018-11-27
申请号：US14733984
申请日：2013-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James D. Hill , Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
Abstract: A seal segment according to an exemplary aspect of the present disclosure includes, among other things, a first axial wall, a second axial wall radially spaced from the first axial wall and a radially outer wall that interconnects the first axial wall and the second axial wall. At least one curved member is radially inwardly offset from the radially outer wall and extending between the first and second axial walls.
-
公开(公告)号：US20160265363A1
公开(公告)日：2016-09-15
申请号：US15033933
申请日：2014-11-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Ioannis Alvanos , Michael G. Abbott , Grant O. Cook, III
CPC classification number: F01D5/147 , F01D5/18 , F01D5/282 , F01D5/284 , F01D5/326 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2230/236 , F05D2230/51 , F05D2240/11 , F05D2240/12 , F05D2300/6033 , Y02T50/672
Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.
Abstract translation: 机翼部件包括具有第一安装座和第一翼片的第一段。 第一段由第一陶瓷基材料形成。 第二段包括第二段安装件和第二段翼型件。 第二段由第二陶瓷基材料形成。 第一和第二段沿着接合接头结合在一起，使得第一和第二安装件彼此接合并且第一和第二翼片彼此接合。
-
Patent Agency Ranking
公开(公告)号：US10179377B2
公开(公告)日：2019-01-15
申请号：US14775964
申请日：2013-12-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L Suciu , Gopal Das , Ioannis Alvanos , Brian D Merry , James D Hill , Allan R Penda
IPC: B23K26/342 , B22F3/105 , B22F5/00 , C22C1/04 , B33Y10/00
Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.
-
公开(公告)号：US20180223668A1
公开(公告)日：2018-08-09
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, JR. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
-
公开(公告)号：US09790792B2
公开(公告)日：2017-10-17
申请号：US14302884
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
CPC classification number: F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.
-
公开(公告)号：US20140294589A1
公开(公告)日：2014-10-02
申请号：US14302884
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
IPC: F01D5/02
CPC classification number: F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.
Abstract translation: 用于燃气涡轮发动机的线轴包括沿着旋转轴线限定的至少一个转子盘和沿着旋转轴线限定的至少一个转子环，转子环与转子盘接触。 转子盘和转子环形成轮廓以限定平滑的转子堆叠负载路径。
-
公开(公告)号：US10794214B2
公开(公告)日：2020-10-06
申请号：US15589009
申请日：2017-05-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Mark F. Zelesky , Ioannis Alvanos , Brian Merry
Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.
-
-
-
-
-
-
-
-
-
Search Results
32
records
(took 0.016 seconds)
