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公开(公告)号：EP2815079A1
公开(公告)日：2014-12-24
申请号：EP13749749.1
申请日：2013-02-14
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
CPC classification number: F23R3/06 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F23R2900/03042 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine component includes a gas path wall having a first surface and second surface and an impingement baffle having impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole extends through the gas path wall. The cooling hole continuously diverges from an inlet in the first surface to an outlet in the second surface such that cross-sectional area of the cooling hole increases continuously from the inlet to the outlet. A longitudinal ridge divides the cooling hole into lobes.
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公开(公告)号：EP2815077A1
公开(公告)日：2014-12-24
申请号：EP13748741.9
申请日：2013-02-12
Applicant: United Technologies Corporation
Inventor： XU, JinQuan , ZELESKY, Mark F. , KOHLI, Atul , GLEINER, Matthew S.
Abstract: A gas turbine engine component includes a cooling hole. The cooling hole includes an inlet, an outlet, a metering section and a diffusing section. The diffusing section extends from the metering section to the outlet and includes a first lobe diverging longitudinally and laterally from the metering section, a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section, and a transition region having a portion that extends between the first and second lobes and an end adjacent the outlet.
Abstract translation: 燃气涡轮发动机部件包括冷却孔。 冷却孔包括入口，出口，计量部分和扩散部分。 扩散部分从计量部分延伸到出口，并且包括从计量部分纵向和横向分开的第一波瓣，与第一波瓣相邻并且从计量部分纵向和横向分开的第二波瓣，以及过渡区域， 在第一和第二凸角和靠近出口的一端之间延伸。
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公开(公告)号：EP2815079B1
公开(公告)日：2020-11-25
申请号：EP13749749.1
申请日：2013-02-14
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
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公开(公告)号：EP2893244B1
公开(公告)日：2020-11-04
申请号：EP13856430.7
申请日：2013-09-06
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
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公开(公告)号：EP3537047A1
公开(公告)日：2019-09-11
申请号：EP19160981.7
申请日：2019-03-06
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
IPC: F23R3/00
Abstract: A combustion liner (300) for an engine (20) includes a shell (302) having an impingement slot (308) disposed therethrough and a panel (304) having an effusion cooling hole disposed therethrough, the effusion cooling hole offset from the impingement slot (308) and configured to create an impingement floatwall film formed between the panel (304) and a combustion chamber of the engine (20). A length of the impingement slot (308) is longer than a width of the impingement slot (308), the length and width configured to create turbulent airflow within a flow channel (306) and minimize particulate matter accumulation. In various embodiments, the length of the impingement slot (308) is at least approximately five or ten times longer than the width.
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Patent Agency Ranking
公开(公告)号：EP3498976A3
公开(公告)日：2019-06-26
申请号：EP18212690.4
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： XU, JinQuan , PROPHETER-HINCKLEY, Tracy A.
Abstract: A turbomachine airfoil element (100) has a substrate. The substrate defines an airfoil having a pressure side and a suction side. A plurality of fiber composite ribs (140A-E) are along the pressure side.
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公开(公告)号：EP3498976A2
公开(公告)日：2019-06-19
申请号：EP18212690.4
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： XU, JinQuan , PROPHETER-HINCKLEY, Tracy A.
CPC classification number: F01D5/145 , F01D5/141 , F01D5/142 , F01D5/28 , F01D5/282 , F01D5/284 , F01D11/08 , F01D11/14 , F01D25/005 , F05D2220/323 , F05D2230/20 , F05D2230/90 , F05D2240/11 , F05D2240/305 , F05D2260/97 , F05D2300/222 , F05D2300/603 , F05D2300/6033 , F05D2300/614
Abstract: A turbomachine airfoil element (100) has a substrate. The substrate defines an airfoil having a pressure side and a suction side. A plurality of fiber composite ribs (140A-E) are along the pressure side.
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公开(公告)号：EP3460191A1
公开(公告)日：2019-03-27
申请号：EP18195433.0
申请日：2018-09-19
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
IPC: F01D5/18
Abstract: A gas turbine engine component has an engine component body and at least one hole (100) formed within the engine component body and extends between a hole inlet (102) and a hole outlet (104). The hole has a first portion (112) with a first roughness and a second portion (114) having a second roughness that is less than the first roughness. The first portion is upstream of the second portion. A gas turbine engine and a method of forming a cooling hole are also disclosed.
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公开(公告)号：EP3108130B1
公开(公告)日：2018-12-12
申请号：EP15751864.8
申请日：2015-01-21
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
CPC classification number: F01D17/145 , F01D11/003 , F01D17/105 , F01D25/12 , F02C3/04 , F02C7/14 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/213 , F05D2300/514 , Y02T50/675
Abstract: A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.
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公开(公告)号：EP2935789B1
公开(公告)日：2018-03-21
申请号：EP13867536.8
申请日：2013-11-06
Applicant: United Technologies Corporation
Inventor： XU, JinQuan
CPC classification number: F01D9/041 , F01D5/143 , Y02T50/673
Abstract: An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.
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