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1. 发明申请

US20140271105A1 TURBINE SHROUD SEGMENT SEALING 有权
标题翻译：涡轮SHROUD部分密封
公开(公告)号：US20140271105A1
公开(公告)日：2014-09-18
申请号：US13799212
申请日：2013-03-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： JOHN PIETROBON , REMY SYNNOTT
IPC分类号： F01D9/02
CPC分类号： F01D11/08 , F01D9/041 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/30 , F05D2250/141 , F05D2250/191 , F05D2250/231 , F05D2260/201
摘要： A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another. The circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween. The inter-segment gaps are sealed by a sealing band mounted to the radially outer surface of the segmented shroud ring so as to extend across the inter-segment gaps around the full circumference of the shroud ring. Impingement jet holes may be defined in the sealing band for cooling the shroud segments.
摘要翻译：分段护罩环围绕燃气涡轮发动机转子的圆周阵列的叶片。护罩环具有多个围绕另一个相邻设置的护罩段。周向相邻的护罩部分具有在其间限定了间隔间间隙的相对侧。跨段间隙由安装在分段护罩环的径向外表面上的密封带密封，以便围绕护罩环的整个圆周延伸跨越段间隙。冲击喷射孔可以限定在密封带中以冷却护罩段。

2. 发明申请

US20170107856A1 SPOKE MOUNTING ARRANGEMENT 审中-公开
公开(公告)号：US20170107856A1
公开(公告)日：2017-04-20
申请号：US15206579
申请日：2016-07-11
申请人： Pratt & Whitney Canada Corp.
发明人： GUY LEFEBVRE , REMY SYNNOTT , JOHN PIETROBON
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F01D25/162 , F05D2230/60 , F05D2260/30 , F05D2260/31
摘要： A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring.

3. 发明申请

US20150226070A1 SHROUDED BLADE FOR A GAS TURBINE ENGINE 有权
标题翻译：气动涡轮发动机喷砂刀片
公开(公告)号：US20150226070A1
公开(公告)日：2015-08-13
申请号：US14179836
申请日：2014-02-13
申请人： Pratt & Whitney Canada Corp.
发明人： GHISLAIN PLANTE , REMY SYNNOTT , JAIDEEP GAHLAWAT
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2220/32 , F05D2240/307
摘要： A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face. Each of the fins has an end disposed toward the pressure side and another end disposed toward the suction side. The ribs extend from and connecting the upstream fin to the downstream fin at locations other than the ends of the upstream and downstream fins. The ribs converge toward the downstream fin at an angle of between about 10 and about 45 degrees. A shroud for a blade is also presented.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片包括平台，叶片根部，限定压力和吸力侧面的翼型部分，以及设置在与叶片根部相对的翼型部分的尖端处的护罩。护罩包括具有与翼型部分相对的径向外表面的主体，上游和下游大体上平行的翅片从外表面向外延伸，以及从外表面向外延伸的两个肋条。每个翅片具有朝向压力侧设置的端部，并且朝向吸力侧设置的另一端部。这些肋从上游翅片和下游翅片的端部之外的位置处延伸并连接到上游翅片到下游翅片。肋以约10度和约45度之间的角度朝向下游翅片会聚。还提供了用于刀片的护罩。

4. 发明申请

US20170114666A1 MULTIPLE SPOKE COOLING SYSTEM AND METHOD 审中-公开
公开(公告)号：US20170114666A1
公开(公告)日：2017-04-27
申请号：US15209065
申请日：2016-07-13
申请人： Pratt & Whitney Canada Corp.
发明人： GUY LEFEBVRE , REMY SYNNOTT
IPC分类号： F01D25/14 , F01D9/06
CPC分类号： F01D25/14 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F02C7/18 , F05D2220/32 , F05D2240/50 , F05D2240/60 , F05D2260/20 , F05D2260/232 , F05D2300/00
摘要： A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. The spokes are used as air feed pipe to provide cooling to different engine systems, such as an oil scupper line and a disc cavity of an adjacent turbine disc.

5. 发明申请

US20170107851A1 MID-TURBINE FRAME SPOKE COOLING SYSTEM AND METHOD 审中-公开
公开(公告)号：US20170107851A1
公开(公告)日：2017-04-20
申请号：US15209089
申请日：2016-07-13
申请人： Pratt & Whitney Canada Corp.
发明人： GUY LEFEBVRE , REMY SYNNOTT , JOHN PIETROBON
IPC分类号： F01D25/12 , F01D25/16 , F02C7/18
CPC分类号： F01D25/14 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F02C7/18 , F05D2220/32 , F05D2240/50 , F05D2240/60 , F05D2260/20 , F05D2260/232 , F05D2300/00
摘要： A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.

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