-
公开(公告)号：WO2015012918A3
公开(公告)日：2015-04-02
申请号：PCT/US2014035419
申请日：2014-04-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： RILEY SARAH , MOORE SASHA M , LEVINE JEFFREY R
CPC classification number: F01D5/186 , F01D5/189 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2240/124 , F05D2240/30 , F05D2260/201 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.
Abstract translation: 用于燃气涡轮发动机的翼型件包括提供外表面和多个径向延伸的冷却通道的外翼型壁。 外表面提供由前缘和后缘连接的压力和吸力面。 冷却通道包括设置在后缘通道上游并与后缘通道流体连通的供给通道。 一个冷却孔从外部翼型壁延伸穿过吸入侧的供给通道到外表面。
-
公开(公告)号：DE602005008311D1
公开(公告)日：2008-09-04
申请号：DE602005008311
申请日：2005-05-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONGILLO JR DOMINIC J , LEVINE JEFFREY R , GREGG SHAWN J , PIETRASZKIEWICZ EDWARD
Abstract: A rotor blade (14) is provided that includes a root (20) and a hollow airfoil (22). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a passage (50) disposed adjacent the leading edge (32), and an axially extending passage (52) disposed adjacent the tip (30). The first passage (50) is connected to the second passage (52). The second passage (52) includes an opening disposed at the trailing edge (34) of the airfoil. A conduit (42) is disposed within the root (20) that is operable to permit airflow through the root (20) and into the leading edge passage (50), wherein the conduit (42) provides the primary path into the leading edge passage (42).
-
3.发明申请
公开(公告)号：WO2013180792A3
公开(公告)日：2014-02-13
申请号：PCT/US2013030332
申请日：2013-03-12
Applicant: UNITED TECHNOLOGIES CORP , LEVINE JEFFREY R , BEATTIE JEFFREY S , STADDON MALCOLM C
Inventor： LEVINE JEFFREY R , BEATTIE JEFFREY S , STADDON MALCOLM C
CPC classification number: F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
Abstract: An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.
Abstract translation: 机翼具有主体，其包括邻接压力侧和吸力侧的前缘和后缘，以提供外部翼型表面。 冷却通道在径向方向上从根部延伸到尖端。 后缘冷却通道将冷却通道与后缘相互连接。 后缘冷却通道包括不同尺寸的第一和第二基座，其相对于具有相同尺寸的基座并且相对于不同尺寸的基座以重复图案布置。
-
公开(公告)号：WO2014007889A2
公开(公告)日：2014-01-09
申请号：PCT/US2013034220
申请日：2013-03-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEVINE JEFFREY R , MONGILLO DOMINIC J , DONNELL BRANDON S
CPC classification number: F01D5/187 , F01D5/145 , F01D5/186 , F01D9/041 , F01D9/065 , F05D2240/122 , F05D2240/304 , F05D2250/12 , F05D2260/202
Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.
Abstract translation: 一种用于燃气涡轮发动机的组件包括第一平台和从第一平台延伸的翼型件。 翼型件包括第一圆角，压力侧偏压排出口和第一中心冷却排出口。 翼型件的压力侧壁和第一平台在后缘处形成锐角。 第一圆角围绕机翼的周边形成，其中翼型件从第一平台延伸。 压力侧偏压的冷却排出口沿着第一圆角外侧的后缘。 每个压力侧偏压的冷却排放口从后缘沿压力侧壁延伸。 第一中心冷却排出口沿着后缘延伸到第一圆角中并且位于压力侧壁和吸力侧壁之间的中心。
-
5.发明申请
公开(公告)号：WO2014143360A3
公开(公告)日：2014-11-06
申请号：PCT/US2013078179
申请日：2013-12-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEVINE JEFFREY R
CPC classification number: F01D5/288 , F01D5/185 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2260/231 , F05D2300/21 , Y10T29/49343
Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.
Abstract translation: 涡轮发动机部件具有具有压力侧，吸力侧和后缘的翼型部。 后缘具有中心排出冷却回路，中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。 翼型部分在压力侧和吸力侧具有热障涂层。 凸表面上的热障涂层在与后缘间隔开的位置处的厚度变薄到零，以便在凸面上留下未涂覆的部分。
-
Patent Agency Ranking
公开(公告)号：WO2013172903A3
公开(公告)日：2014-01-09
申请号：PCT/US2013027232
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEVINE JEFFREY R , GREGG SHAWN J
CPC classification number: F01D5/188 , Y02T50/676
Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.
Abstract translation: 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面，并且从根部到尖端部分径向延伸，根部和末端部分限定了它们之间的跨度。 热涂层从翼型的根部朝向翼型的末端部分延伸。 与根部中的最小跨度相比，热涂层的相对涂层厚度在末端部分的全跨度处降低至少30％。
-
公开(公告)号：DE602005022018D1
公开(公告)日：2010-08-12
申请号：DE602005022018
申请日：2005-05-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEVINE JEFFREY R , PIETRASZKIEWICZ EDWARD
-
公开(公告)号：SG122911A1
公开(公告)日：2006-06-29
申请号：SG200507274
申请日：2005-11-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , PIETRASZKIEWICZ EDWARD F , KONTROVITZ DAVID M , LEVINE JEFFREY R , CHON YOUNG , MONGILLO DOMINIC , TELLER BRET
Abstract: An airfoil (59), and in a disclosed embodiment a rotor blade, has film cooling holes (48) formed at a leading edge (41). A supplemental film cooling channel (60) is positioned near the leading edge (41), but spaced toward the trailing edge from the leading edge. The supplemental film cooling channel (60) directs film cooling air onto a suction wall (38). The supplemental film cooling channel air is generally directed to a location on the suction wall (38) that has raised some challenges in the past. In a disclosed embodiment, the airfoil is provided with a thermal barrier coating, and the supplemental film cooling air protects this thermal barrier coating.
-
9.发明公开TAPERED THERMAL BARRIER COATING ON CONVEX AND CONCAVE TRAILING EDGE SURFACES 审中-公开康奈尔·肯尼亚·肯尼亚·弗朗西斯科
公开(公告)号：EP2956623A4
公开(公告)日：2016-03-16
申请号：EP13877747
申请日：2013-12-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEVINE JEFFREY R
CPC classification number: F01D5/288 , F01D5/185 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/312 , F05D2230/313 , F05D2260/231 , F05D2300/21 , Y10T29/49343
Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.
Abstract translation: 涡轮发动机部件具有具有压力侧，吸力侧和后缘的翼型部。 后缘具有中心排出冷却回路，其中心排出冷却回路具有由翼型部的压力侧的凹面界定的出口和翼型部的吸入侧的凸面。 翼型部分在压力侧和吸力侧具有热障涂层。 凸表面上的隔热涂层在与后缘间隔开的位置处的厚度变薄到零，以便在凸面上留下未涂覆的部分。
-
10.发明公开
公开(公告)号：EP2841711A4
公开(公告)日：2016-06-01
申请号：EP13796983
申请日：2013-03-12
Applicant: UNITED TECHNOLOGIES CORP , LEVINE JEFFREY R , BEATTIE JEFFREY S , STADDON MALCOLM C
Inventor： LEVINE JEFFREY R , BEATTIE JEFFREY S , STADDON MALCOLM C
CPC classification number: F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
Abstract: An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.
-
-
-
-
-
-
-
-
-
Search Results
15
records
(took 0.022 seconds)
