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公开(公告)号：US20140058644A1
公开(公告)日：2014-02-27
申请号：US13954541
申请日：2013-07-30
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
IPC: B64D31/06
Abstract: A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight operation controller, that an airplane is in a first flight condition, wherein the first flight condition is associated with a first turbine clearance and a first engine responsiveness level, determining, with the flight operation controller, that the airplane is in a second flight condition, adjusting an engine responsiveness level from the first engine responsiveness level to a second engine responsiveness level based on determining the airplane is in the second flight condition, and adjusting the turbine clearance from the first turbine clearance to a second turbine clearance based on the engine responsiveness level.
Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮间隙的方法。 所述方法包括使用飞行操作控制器确定飞机处于第一飞行状态，其中第一飞行条件与第一涡轮机间隙和第一发动机响应度水平相关联，用飞行操作控制器确定： 飞机处于第二飞行状态，基于确定飞机处于第二飞行状态，将发动机响应性水平从第一发动机响应水平调整到第二发动机响应水平，并且将涡轮机间隙从第一涡轮机间隙调整到第二飞行器间隙 基于发动机响应性水平的涡轮间隙。
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公开(公告)号：US20140301861A1
公开(公告)日：2014-10-09
申请号：US14172435
申请日：2014-02-04
Applicant: General Electric Company
Inventor： Robert William Bruce , Aaron Dennis Gastrich , John William Hanify , Roger Owen Barbe
CPC classification number: F01D5/28 , C23C16/44 , F01D5/288 , F04D29/023 , F04D29/324 , F05D2230/313 , F05D2240/121 , F05D2240/303 , F05D2300/228 , F05D2300/611 , Y02T50/671 , Y02T50/673
Abstract: A compressor blade having an airfoil that comprises oppositely-disposed convex and concave surfaces, oppositely-disposed leading and trailing edges defining therebetween a chord length of the airfoil, a forward-most nose of the airfoil located at the leading edge and having a profile, a blade tip, and an erosion-resistant coating. The coating is present on the concave surface near the trailing edge, optionally present on the nose, optionally present on the convex surface, wherein the convex surface is free of the erosion resistant coating within at least 20% of the chord length from the nose. The thickness of the coating on the concave surface, the convex surface, and the nose is such that, if the gas turbine engine is exposed to an erosive environment, deterioration of the concave surface, the convex surface and the leading edge does not form a pronounced cusp at an intersection of the convex surface and leading edge.
Abstract translation: 一种压缩机叶片，其具有包括相对设置的凸形和凹形表面的翼型，相对设置的前缘和后缘在其间限定翼型的弦长，位于前缘并具有轮廓的翼型的最前端， 叶片尖端和耐侵蚀涂层。 涂层存在于靠近后缘的凹面上，任选地存在于鼻部上，任选存在于凸表面上，其中凸起表面在距离鼻子的弦长的至少20％内没有抗侵蚀涂层。 凹面，凸面，鼻部的涂层厚度使得如果燃气涡轮发动机暴露于侵蚀环境，则凹面，凸面和前缘的劣化不会形成 在凸面和前缘的交点处发音尖。
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公开(公告)号：US09758252B2
公开(公告)日：2017-09-12
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
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公开(公告)号：US20160311546A1
公开(公告)日：2016-10-27
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮机间隙的方法。 该方法包括确定飞机处于第一飞行状态，并且将涡轮机间隙间隙调整到与第一飞行状态相关联的第一间隙间隙距离。 该方法还包括确定对第二飞行状态的需求，以及调整发动机对功率参数的第一预定变化的第一发动机响应性的发动机响应性。 该方法还包括将引擎响应性从第一发动机响应级别降低到用于发动机的功率参数的第二预定变化的第二发动机响应性水平，并且在第二预定变化期间关闭与护罩相关联的间隙控制阀 发动机的功率参数。
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