-
公开(公告)号：US10107115B2
公开(公告)日：2018-10-23
申请号：US14764760
申请日：2014-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ioannis Alvanos
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a static structure that extends between a radially outer portion and a radially inner portion and at least one vortex creation feature formed on the static structure.
-
公开(公告)号：US20150377073A1
公开(公告)日：2015-12-31
申请号：US14769801
申请日：2014-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Gopal Das , Ioannis Alvanos , Brian D. Merry
CPC classification number: F01D25/30 , B21K7/12 , B23K31/02 , F01D25/162 , F02C3/04 , F02C7/20 , F02K1/78 , F05D2220/30 , F05D2230/236 , F05D2230/25 , F05D2230/60 , F05D2300/174 , Y02T50/672
Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
Abstract translation: 用于燃气涡轮发动机的涡轮机排气箱包括在CMC核心机舱后部和CMC尾锥之间的多个CMC涡轮机排气外壳支柱。
-
23.发明授权公开(公告)号：US10240471B2
公开(公告)日：2019-03-26
申请号：US14767728
申请日：2013-11-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ioannis Alvanos
IPC: F04D29/68 , F04D29/52 , F01D11/08 , F04D29/16 , F01D11/12 , F01D11/00 , F01D11/02 , F04D29/32 , F01D5/02 , F01D9/04 , F01D25/24 , F02C3/06 , F02C3/14
Abstract: An axial flow compressor is disclosed with a plurality of rotors. Each rotor includes a disk having an outer rim. Each outer rim is coupled to a radially outwardly extending rotor blade. The case is coupled to a plurality of radially inwardly extending stator vanes, i.e. cantilever-type stator vanes. Each stator vane is disposed between two rotor blades and extends towards one of the outer rims and terminates at a tip disposed in close proximity to one of the outer rims. At least one of the outer rims includes a serrated outer surface that faces the tip of a stator vane which results in a vortex flow causing air that would normally leak through the clearance between the stator vane and the outer rim to engage the stator vane to a greater degree thereby increasing the efficiency of the compressor.
-
公开(公告)号：US20180328207A1
公开(公告)日：2018-11-15
申请号：US16044611
申请日：2018-07-25
Applicant: United Technologies Corporation
Inventor： Ioannis Alvanos
CPC classification number: F01D9/041 , F01D5/20 , F01D11/001 , F04D29/164 , F04D29/544 , F05D2220/32 , F05D2240/125 , F05D2240/127 , F05D2240/129 , F05D2250/18 , F05D2250/182 , F05D2250/183 , F05D2250/294
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a static structure that extends between a radially outer portion and a radially inner portion and at least one vortex creation feature formed on the static structure. A method of sealing is also disclosed.
-
公开(公告)号：US10125620B2
公开(公告)日：2018-11-13
申请号：US14906618
申请日：2014-06-19
Applicant: United Technologies Corporation
Inventor： Ioannis Alvanos
Abstract: A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.
-
Patent Agency Ranking
公开(公告)号：US20180320542A1
公开(公告)日：2018-11-08
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
IPC: F01D11/24
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.
-
公开(公告)号：US10060354B2
公开(公告)日：2018-08-28
申请号：US15445521
申请日：2017-02-28
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：US09976485B2
公开(公告)日：2018-05-22
申请号：US14695142
申请日：2015-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Ioannis Alvanos
CPC classification number: F02C7/185 , F01D5/081 , F01D25/125 , F02C6/08 , F02C7/06 , F05D2220/32 , F05D2260/232
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger configured to exchange heat with a bleed airflow to provide a conditioned airflow. A bearing compartment is in fluid communication with the heat exchanger, and a first passageway communicates the conditioned airflow to the bearing compartment. The conditioned airflow is communicated radially between a bearing housing of the bearing compartment and a diffuser case and a nozzle assembly in fluid communication with the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment and then through a plurality of openings of the nozzle assembly.
-
公开(公告)号：US20160186583A1
公开(公告)日：2016-06-30
申请号：US14906618
申请日：2014-06-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ioannis Alvanos
IPC: F01D5/30
CPC classification number: F01D5/3084 , B23P15/04 , C04B35/71 , C04B37/006 , C04B37/026 , C04B2237/086 , C04B2237/121 , C04B2237/122 , C04B2237/123 , C04B2237/124 , C04B2237/125 , C04B2237/127 , C04B2237/128 , C04B2237/16 , C04B2237/365 , C04B2237/368 , C04B2237/38 , C04B2237/405 , C04B2237/62 , C04B2237/72 , C04B2237/76 , C04B2237/80 , F01D5/282 , F01D5/284 , F01D5/3007 , F01D9/041 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite.
Abstract translation: 燃气涡轮发动机翼型组件包括分别结合到平台的相对侧的翼型件和附接结构。 翼型件，平台和附接结构中的至少一个由陶瓷基复合材料构成。
-
公开(公告)号：US20160153286A1
公开(公告)日：2016-06-02
申请号：US14905351
申请日：2014-07-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Ioannis Alvanos
CPC classification number: F01D5/28 , F01D5/34 , F01D11/122 , F01D11/18 , F02C3/04 , F05D2300/174 , Y02T50/671
Abstract: A turbine module comprises a stator assembly disposed annularly about a rotor assembly. The rotor assembly includes a plurality of turbine blades circumferentially distributed about a turbine disk. The stator assembly includes at least one case segment and an abradable surface disposed radially adjacent to a tip of each of the plurality of rotor blades. The turbine blades each include an airfoil section with a first gamma-phase titanium aluminide (gamma-TiAl) substrate, and the at least one case segment has a second gamma-TiAl substrate.
Abstract translation: 涡轮机模块包括围绕转子组件环形设置的定子组件。 转子组件包括绕涡轮盘周向分布的多个涡轮机叶片。 定子组件包括至少一个壳体段和位于径向相邻于多个转子叶片中的每一个的尖端的可磨损表面。 涡轮机叶片各自包括具有第一γ相钛铝化物（γ-TiAl）衬底的翼型部分，并且所述至少一个壳段具有第二γ-TiAl衬底。
-
-
-
-
-
-
-
-
-
Search Results
32
records
(took 0.019 seconds)
