-
公开(公告)号：US20180229850A1
公开(公告)日：2018-08-16
申请号：US15433645
申请日：2017-02-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Daniel ALECU
CPC classification number: B64D15/02 , B64D2033/0233 , F02C7/047 , F05D2260/213 , F05D2260/232 , Y02T50/672 , Y02T50/675
Abstract: An anti-icing system for a gas turbine engine comprises a closed circuit containing a change-phase fluid, at least one heating component for boiling the change-phase fluid, the anti-icing system configured so that the change-phase fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the change-phase fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the change-phase fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed change-phase fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.
-
公开(公告)号：US20170211477A1
公开(公告)日：2017-07-27
申请号：US15007527
申请日：2016-01-27
Applicant: Pratt & Whitney Canada Corp.
Inventor： David MENHEERE , Andrew MARSHALL
CPC classification number: F01D25/20 , F01D19/00 , F02C7/32 , F02C7/36 , F05D2260/98 , H02P29/20 , H02P2101/00
Abstract: An oil system of a turbine engine and a method for driving an oil pump of such oil system are disclosed. In various embodiments, the oil system comprises an oil pump for fluid communication with one or more lubrication loads of the turbine engine, a first source of motive power and a coupling device. The first source of motive power is drivingly engaged to the oil pump for driving the oil pump during a first mode of operation. The coupling device is configured to drivingly disengage a second source of motive power from the oil pump during the first mode of operation and drivingly engage the second source of motive power with the oil pump to drive the oil pump during a second mode of operation.
-
公开(公告)号：US20170037774A1
公开(公告)日：2017-02-09
申请号：US15227318
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony JONES , Andre JULIEN , David MENHEERE , Jean THOMASSIN , Richard ULLYOTT , Daniel VAN DEN HENDE
Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.
Abstract translation: 用于飞行器的辅助动力单元包括旋转间歇内燃机，具有与发动机的出口流体连通的入口的涡轮机，与发动机混合的涡轮，具有与所述发动机的环境流体连通的入口的压缩机 飞机和与飞机流体连通的出口，压缩机可独立于涡轮机旋转，驱动地接合到压缩机的电动机和驱动地接合到发动机的转移发电机，转移发电机和电动机电连接以允许 电力传输。 压缩机或额外的压缩机可以与发动机的入口流体连通。 还讨论了一种操作飞行器的辅助动力单元的方法。
-
公开(公告)号：US20160298541A1
公开(公告)日：2016-10-13
申请号：US15188277
申请日：2016-06-21
Applicant: Pratt & Whitney Canada Corp.
Inventor： Andreas ELEFTHERIOU , David MENHEERE , Daniel ALECU
CPC classification number: F02C7/08 , F05D2220/323 , F05D2230/60 , F05D2230/642 , F28D9/0018 , F28D21/001 , F28F9/0236 , F28F9/26 , F28F21/087 , F28F2230/00 , F28F2265/26 , Y10T29/49716
Abstract: A method of installing a segment of a recuperator within an exhaust duct of a gas turbine engine, including positioning the segment such that its exhaust inlet is in fluid flow communication with the turbine section and its exhaust outlet is adapted to deliver an exhaust flow to atmosphere, engaging its air inlet to a plenum in fluid flow communication with the compressor discharge, and engaging its air outlet to another plenum containing the combustor. One of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding plenum, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the corresponding plenum. The floating connection allows relative movement of the segment within the exhaust duct.
Abstract translation: 一种在燃气涡轮发动机的排气管道内安装换热器的一段的方法，包括将所述段定位成使得其排气入口与涡轮部分及其排气出口流体流动连通的方法适于将排气流输送到大气 将其空气入口接合到与压缩机排放流体流动连通的增压室，并将其空气出口接合到包含燃烧器的另一个通风室。 与空气入口接合并接合空气出口的一个包括形成刚性连接，提供与相应的通风室的密封的流体流动连通，并且接合空气入口并与空气出口接合的另一个包括形成浮动连接，提供密封的流体流动连通 相应的会议厅。 浮动连接允许段在排气管道内的相对运动。
-
25.发明申请公开(公告)号：US20150200580A1
公开(公告)日：2015-07-16
申请号：US14667768
申请日：2015-03-25
Applicant: Pratt & Whitney Canada Corp.
Inventor： David MENHEERE , Andreas ELEFTHERIOU , Richard KOSTKA
CPC classification number: H02K7/1823 , H02K15/02 , H02K15/16 , Y10T29/49002 , Y10T29/49009 , Y10T29/49012
Abstract: A method of assembling a starter/generator in a gas-turbine engine, including coupling a rotor and a stator of the starter/generator such that the rotor is rotatable with respect to the stator to drive the rotor when the starter/generator is electrically powered and to produce electrical power when the rotor is rotated, securing the stator to a bearing support, coupling the starter/generator to a low pressure shaft of the engine by installing the bearing support over a bearing assembly secured to an end of the low pressure shaft, inserting the low pressure shaft through a high pressure shaft of the engine with the end of the low pressure shaft protruding therefrom and positioning the starter/generator in proximity of an end of the high pressure shaft, and drivingly engaging the rotor to the high pressure shaft.
Abstract translation: 一种在燃气涡轮发动机中组装起动器/发电机的方法，包括联接起动器/发电机的转子和定子，使得当起动器/发电机被电动时，转子可相对于定子旋转以驱动转子 并且当转子旋转时产生电力，将定子固定到轴承支撑件上，通过将轴承支撑件安装在固定到低压轴的端部的轴承组件上来将起动器/发电机连接到发动机的低压轴 将低压轴穿过发动机的高压轴，低压轴的端部从其突出，将起动器/发电机定位在靠近高压轴的端部处，并将转子驱动地接合到高压 轴。
-
Patent Agency Ranking
公开(公告)号：US20150099453A1
公开(公告)日：2015-04-09
申请号：US14048186
申请日：2013-10-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andreas ELEFTHERIOU , Daniel ALECU , David MENHEERE
CPC classification number: F02C7/08 , B21D15/12 , B21D53/06 , F28D7/0041 , F28D7/082 , F28D21/001 , F28D2021/0026 , F28F1/02 , F28F1/025 , Y10T29/49357
Abstract: A method of manufacturing a recuperator segment uses metal tubes deformed into air cells in a waved configuration. The air cells are stacked one to another to form a double skinned recuperator segment providing cold air passages through the respective air cells and hot gas passages through spaces between adjacent air cells.
Abstract translation: 制造换热器部件的方法使用以波形配置变形为气泡的金属管。 空气池彼此堆叠以形成双皮层换热器段，其提供通过各个空气室的冷空气通道和通过相邻空气室之间的空间的热气通道。
-
公开(公告)号：US20240309803A1
公开(公告)日：2024-09-19
申请号：US18185007
申请日：2023-03-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE
CPC classification number: F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
Abstract: An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
-
公开(公告)号：US20220389837A1
公开(公告)日：2022-12-08
申请号：US17337621
申请日：2021-06-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE
Abstract: An engine bi-material joint includes a first flange composed of a first material and defining a first coefficient of thermal expansion, and a second flange composed of a second material and defining a second coefficient of thermal expansion. The second flange is different from the first material. An interface flange is engaged with the first flange and with the second flange. The interface flange defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion of the first flange. The third coefficient of thermal expansion is less than the second coefficient of thermal expansion of the second flange. The first coefficient of thermal expansion of the first flange is less than the second coefficient of thermal expansion of the second flange.
-
公开(公告)号：US20210324797A1
公开(公告)日：2021-10-21
申请号：US16849508
申请日：2020-04-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Santo CHIAPPETTA , Tim REDFORD , Daniel VAN DEN ENDE
Abstract: An inertial particle separator (IPS) for a gas turbine engine, has: a plenum circumferentially extending about a central axis and defined between an outer wall and an inner wall, the plenum having an inlet facing a circumferential direction relative to the central axis, a radius of the outer wall decreasing in an axial direction relative to the central axis between the inlet and an annular splitter extending circumferentially around the central axis and located downstream of the inlet radially between the outer wall and the inner wall, a particle outlet including an annulus radially between the outer wall and the splitter, an air outlet fluidly connectable to a compressor of the gas turbine engine and defined radially between the splitter and the inner wall.
-
公开(公告)号：US20210324795A1
公开(公告)日：2021-10-21
申请号：US16849364
申请日：2020-04-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Santo CHIAPPETTA , Tim REDFORD , Daniel VAN DEN ENDE
Abstract: An inertial particle separator (IPS) for a gas turbine engine, has: inner and outer walls extending about a central axis, an inlet defined between the inner and outer walls and oriented axially; swirling vanes extending at least radially between the inner and outer walls and circumferentially distributed around the central axis, the swirling vanes configured for inducing a circumferential component in an airflow flowing between the swirling vanes; a plenum between the inner and outer walls downstream of the swirling vanes, the plenum circumferentially extending about the central axis, the outer wall converging toward the central axis in a direction of the airflow; and a splitter radially between the inner and outer walls downstream of the plenum and circumferentially extending around the central axis, a particle outlet radially between the splitter and the outer wall, an air outlet radially between the inner wall and the splitter.
-
-
-
-
-
-
-
-
-
Search Results
47
records
(took 0.016 seconds)
