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1. 发明专利

JPH1047003A ROTOR ASSEMBLY TO BE COOLED OF TURBINE ENGINE 失效
公开(公告)号：JPH1047003A
公开(公告)日：1998-02-17
申请号：JP9563397
申请日：1997-04-14
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F
IPC分类号： F01D5/06 , F01D5/08 , F01D5/30 , F01D11/00 , F02B77/02 , F02C7/18
摘要： PROBLEM TO BE SOLVED: To cause flow of turbine cooling air, leaking from a cooling air flow passage, for use again, and to effect the use of leak air caused to flow again for cooling a machine element exposed to hot gas passing through the main gas passage of an engine. SOLUTION: A rotor assembly to be cooled for a gas turbine engine comprises rotor blade plates 48; and a plurality of cover plates supported in the blade plate mounting groove of a rotor disc 30. The blade plate has a platform 46 having a rear edge 58, and each cover plate contains at least one conduit to extract leak air from a plenum 102 in front of a disc to cool a rear edge and collide the air with a platform rear edge 58. Each conduit is specified by the front of a blade plate root 40 and a groove formed in the cover plate. Leak air is productively used in a way that leak air uses to cool the rear edge of a platform rather than the air is caused to uselessly flow in an engine gas passage situated near a platform front edge 56.

2. 发明专利

JP2002167636A LOW DENSITY OXIDATION RESISTANT SUPERALLOY MATERIAL CAPABLE OF THERMAL BARRIER COATING RETENTION WITHOUT BOND COAT 审中-公开
公开(公告)号：JP2002167636A
公开(公告)日：2002-06-11
申请号：JP2001330211
申请日：2001-10-29
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F , GUPTA DINESH K , ALAN D SETEL
IPC分类号： C22C19/05 , C23C8/12 , C23C28/00 , C23C28/04 , F01D5/28
摘要： PROBLEM TO BE SOLVED: To provide a low density superalloy and no bond coat thermal barrier system. SOLUTION: The combination of an alloy and a TBC system can be used to fabricate lightweight turbine blades with reduced blade pull. The alloy has a composition substantially consisting of, by weight, about 7 to about 13% Cr, about 4.5 to about 6.7% Al, about 0.5 to about 2% Ti, about 3 to about 12% W, about

3. 发明专利

JP2002188406A ROTOR BLADE FOR AXIAL FLOW ROTARY MACHINE 失效
公开(公告)号：JP2002188406A
公开(公告)日：2002-07-05
申请号：JP2000366583
申请日：2000-12-01
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F , MONGILLO DOMINIC J JR
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a cooling structure for a trailing edge region of a rotor blade, having an acceptable level of capability of being cast for its manufacture, as well as blade stress and metal temperature at an acceptable level under the running conditions. SOLUTION: An airfoil has heat transfer parts (106, 108, 112) at its rearmost part of the trailing edge region, and these heat transfer parts include a row of flow dividers (112) that extend in the direction of the vane chord. At least one of these flow dividers (112) includes a sidewall (144) that radially faces inward and a sidewall (142) that radially faces outward, with a diffusion angle αof the sidewall (144) radially facing inward being greater than diffusion angel βof the sidewall (142) radially facing outward.

4. 发明专利

JP2001164904A COOLING TYPE FLUID REACTION ELEMENT FOR TURBOMACHINERY 失效
公开(公告)号：JP2001164904A
公开(公告)日：2001-06-19
申请号：JP2000364275
申请日：2000-11-30
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F
IPC分类号： F01D9/02 , F01D5/18
摘要： PROBLEM TO BE SOLVED: To perform effective cooling by a cooling film by effectively utilizing a refrigerant, to prevent excessive discharge of a refrigerant in a region on the low pressure side, and to reduce a stress of a wall. SOLUTION: The airfoil 16 of a cooling type vane 12 is provided with a pair of ribs 42 and 44, having no hole, laterally extending across an internal part. The rib is provided with end parts 52 and 56 on the suction side and end parts 54 and 58 on the pressure side. The range of a segment Ss is determined in the direction of a chord by the end part on the suction side and an internal part filling chamber 48 is partitioned thereby. The filling chamber distributes a pressure refrigerant in the direction of an air foil length. The row 84 of a film cooling hole is extended through the segment Ss of the wall on the suction side and forms single passage through which a refrigerant is carried from the filling chamber to a working fluid flow passage. The rib end parts 52 and 56 on the suction side are positioned astride a minimum fluid pressure point on a surface 38 on the suction side and an active outflow of a refrigerant and film continuity in the direction of airfoil direction are achieved by a minimum pressure refrigerant, and the stress of the wall segment Ss is reduced.

5. 发明专利

JP2001065306A COOLABLE STATOR VANE FOR ROTATING MACHINE 失效
公开(公告)号：JP2001065306A
公开(公告)日：2001-03-13
申请号：JP2000233872
申请日：2000-08-02
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F , STEUBER GARY D , KANE DANIEL E , MERRY BRIAN
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04
摘要： PROBLEM TO BE SOLVED: To provide a comparatively simple cooling flow passage for rear end area of a stator vane. SOLUTION: A platform for the stator vane includes a meandering flow passage 168 for cooling fluid including two paths 169, 170 provided in the rear end area of the vane. The meandering flow passage 168 extends to a side, folds back and makes flow flowing backward. An endmost part of the meandering flow passage 168 is adjacent to the rear end 134 so as to accept at least the half flow flowing into the flow passage 168 and to discharge the flow through a gas flow passage surface and the rear end 134 of the platform.

6. 发明专利

JPH11107702A COOLABLE AIRFOIL 失效
公开(公告)号：JPH11107702A
公开(公告)日：1999-04-20
申请号：JP22391698
申请日：1998-08-07
申请人： UNITED TECHNOLOGIES CORP
发明人： KRAUSE DAVID A , MONGILLO DOMINIC J JR , SOECHTING FRIEDRICH O , ZELESKY MARK F
IPC分类号： F01D5/18
摘要： PROBLEM TO BE SOLVED: To provide a coolable airfoil or vane, which can operate at a high temperature for a long time but requires a minimal amount of coolant. SOLUTION: A blade or vane for a gas turbine engine includes a main cooling system 42 having a series of intermediate passages 44, 46a, 46b, 46c, and 48, and a subordinate cooling system 92 having a series of cooling ducts 94 (94a to 94h). The ducts of subordinate cooling system 92, being parallel to and having the same radial extent with the intermediate passages, are installed between the intermediate passages 44, etc., and outer surface 28 of the airfoil and within a surrounding wall 16. The ducts are installed within high temperature load regions 104 and 106 in the direction of a chord so as to maximize efficiency. The ducts are recommended to have the same extent in the direction of a chord in several intermediate passages in order to avoid an excessive rise in coolant temperature within the intermediate passages. The length of the duct in the direction of a chord is limited so as not to generate a temperature gradient, with could lead to failure, at airfoil wall 16.

7. 发明申请

WO2014120324A2 TURBINE ENGINE COOLING SYSTEM WITH AN OPEN LOOP CIRCUIT 审中-公开
标题翻译：带有开环回路的涡轮发动机冷却系统
公开(公告)号：WO2014120324A2
公开(公告)日：2014-08-07
申请号：PCT/US2013070362
申请日：2013-11-15
申请人： UNITED TECHNOLOGIES CORP
发明人： BLAIR MICHAEL F , PROPHETER-HINCKLEY TRACY A , ZELESKY MARK F
CPC分类号： F01D25/12 , F01D25/10 , F02C7/14 , F05D2260/205 , F05D2260/213 , F05D2260/232 , F28D15/00 , F28F1/124 , F28F1/40 , F28F7/02 , F28F2255/18 , Y02T50/676
摘要： A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
摘要翻译：涡轮发动机系统包括热源，热交换器，冷却介质入口和冷却介质出口。热源包括第一通道。热交换器包括第二通道和第三通道。第一和第二通道配置在闭环电路中。第三通道在开环电路中配置在入口和出口之间。

8. 发明申请

WO2015112273A2 TIP LEAKAGE FLOW DIRECTIONALITY CONTROL 审中-公开
标题翻译： TIP泄漏流动方向控制
公开(公告)号：WO2015112273A2
公开(公告)日：2015-07-30
申请号：PCT/US2014069424
申请日：2014-12-10
申请人： UNITED TECHNOLOGIES CORP
发明人： ZELESKY MARK F , AGGARWALA ANDREW S
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/126 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.
摘要翻译：除了别的之外，根据本公开的示例性方面的翼型包括吸入侧壁和压力侧壁，每个侧壁从翼型基部沿翼展方向延伸并且在前缘和后缘之间沿弦向延伸。尖端壁从前缘向后缘弦向延伸并且连接吸入和压力侧壁的相应的外部翼展方向端部。尖端泄漏控制通道凹入尖端壁中，尖端泄漏控制通道包括在第一控制通道叶片侧壁与由相应尖端泄漏控制叶片建立的第二控制通道叶片侧壁之间延伸的控制通道底板。内部冷却腔设置在吸入侧壁和压力侧壁之间，并且通道冷却孔将来自内部冷却腔的气流供给到尖端泄漏控制通道。

9. 发明申请

WO2013165511A3 EDM METHOD FOR MULTI-LOBED COOLING HOLE 审中-公开
标题翻译：多孔冷却孔的电火花加工方法
公开(公告)号：WO2013165511A3
公开(公告)日：2014-01-03
申请号：PCT/US2013025716
申请日：2013-02-12
申请人： UNITED TECHNOLOGIES CORP
发明人： LEVASSEUR GLENN , PIETRASZKIEWICZ EDWARD F , ZELESKY MARK F , MONGILLO DOMINIC J , KLINEFELTER KEVIN J , DOLL STEPHEN D , FRITCH MARKUS W
IPC分类号： F02C7/18 , F01D5/08 , F01D25/12 , F02K3/00
CPC分类号： B23H9/10 , B23H1/00 , B23H7/26 , B23H9/14 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/676
摘要： A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.
摘要翻译：用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘，并在扩散段中形成纵向凸起。计量部分从壁的第一表面上的入口延伸到壁的第二表面。扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。

10. 发明申请

WO2015023322A3 METHOD FOR DETECTING A COMPROMISED COMPONENT 审中-公开
标题翻译：检测压缩组件的方法
公开(公告)号：WO2015023322A3
公开(公告)日：2015-04-16
申请号：PCT/US2014033341
申请日：2014-04-08
申请人： UNITED TECHNOLOGIES CORP
发明人： GREENBERG MICHAEL D , ZELESKY MARK F
IPC分类号： G01N21/95 , C23C4/06 , F01D5/12 , F01D25/00 , F02C7/24 , G01J5/48
CPC分类号： F01D5/288 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/34 , C23C28/3455 , F01D5/186 , F01D21/003 , F05D2220/32 , F05D2260/202 , F05D2260/80 , G01J5/48 , G01N21/8803 , G01N21/95
摘要： A method for providing visually detectable changes to a surface that has been subjected to a temperature in excess of a predetermined temperature. A coating is applied to the surface, wherein the coating will melt when the predetermined temperature has been reached. Centrifugal forces acting on the melted coating will cause it to be displaced such that the disturbed surface is visibly detectable upon inspection after solidifying.
摘要翻译：一种用于向已经经受超过预定温度的温度的表面提供视觉可检测变化的方法。将涂层施加到表面上，其中当达到预定温度时涂层会熔化。作用在熔融涂层上的离心力将使其移动，从而在固化后检查时可以明显地检测到受干扰的表面。

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