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公开(公告)号：US20130078080A1
公开(公告)日：2013-03-28
申请号：US13613783
申请日：2012-09-13
IPC分类号： F01D25/12
CPC分类号： F01D25/125 , F01D9/065 , F01D11/04 , Y02T50/675
摘要： A mid-turbine frame is disposed between high and low pressure turbine assemblies. A secondary air system is defined in the mid-turbine frame (MTF) to provide cooling to the turbine section of the engine. The secondary air system may be used to cool and pressurize seals to assist with oil retention in bearing cavities. The temperature gain of the secondary air may be reduced by flowing the secondary air through one or more external lines and then generally radially inwardly through air passages defined in the MTF.
摘要翻译： 中涡轮机架布置在高压和低压涡轮机组件之间。 在中涡轮机架（MTF）中限定二次空气系统，以向发动机的涡轮机部分提供冷却。 二次空气系统可用于冷却和加压密封件，以有助于轴承腔中的保油。 二次空气的温度增益可以通过使二次空气通过一个或多个外部管线然后通常径向向内通过在MTF中限定的空气通道而减小。
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公开(公告)号：US09279341B2
公开(公告)日：2016-03-08
申请号：US13613783
申请日：2012-09-13
CPC分类号： F01D25/125 , F01D9/065 , F01D11/04 , Y02T50/675
摘要： A mid-turbine frame is disposed between high and low pressure turbine assemblies. A secondary air system is defined in the mid-turbine frame (MTF) to provide cooling to the turbine section of the engine. The secondary air system may be used to cool and pressurize seals to assist with oil retention in bearing cavities. The temperature gain of the secondary air may be reduced by flowing the secondary air through one or more external lines and then generally radially inwardly through air passages defined in the MTF.
摘要翻译： 中涡轮机架布置在高压和低压涡轮机组件之间。 在中涡轮机架（MTF）中限定二次空气系统，以向发动机的涡轮机部分提供冷却。 二次空气系统可用于冷却和加压密封件，以有助于轴承腔中的保油。 二次空气的温度增益可以通过使二次空气通过一个或多个外部管线然后通常径向向内通过在MTF中限定的空气通道而减小。
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公开(公告)号：US08371127B2
公开(公告)日：2013-02-12
申请号：US12572066
申请日：2009-10-01
申请人： Eric Durocher , Pierre-Yves Legare
发明人： Eric Durocher , Pierre-Yves Legare
IPC分类号： F02C7/12
CPC分类号： F01D5/082 , F01D9/065 , F01D11/001 , F01D11/02 , F01D25/125 , F01D25/162 , F02C7/12 , F02C7/18
摘要： A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for containing pressurized cooling air to cool the inter-turbine duct and the hollow struts, and discharges the used cooling air to further cool respective high and low pressure turbine assemblies.
摘要翻译： 中间涡轮机框架设置在高压和低压涡轮机组件之间。 限定在燃气涡轮发动机的中间涡轮机框架中的冷却空气系统包括用于容纳加压冷却空气以冷却涡轮机间管道和中空支柱的内部空腔，并且排放所使用的冷却空气以进一步冷却相应的高压和低压涡轮机 装配。
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公开(公告)号：US08453464B2
公开(公告)日：2013-06-04
申请号：US12571987
申请日：2009-10-01
申请人： Eric Durocher , Pierre-Yves Legare
发明人： Eric Durocher , Pierre-Yves Legare
IPC分类号： F02C7/20
摘要： An air metering apparatus for a secondary air system of gas turbine engine includes a metering gap defined between surfaces comprised of one or more metals having one of similar coefficients of thermal expansion or similar thermal expansions at an operating temperature. Provided is an air metering gap which undergoes thermal growth in a way which provides a suitable air metering gap during engine running conditions.
摘要翻译： 用于燃气涡轮发动机的二次空气系统的空气计量装置包括限定在由一种或多种金属构成的表面之间的计量间隙，所述金属具有在工作温度下具有相似的热膨胀系数或相似的热膨胀系数之一。 提供了一种空气计量间隙，其在发动机运行条件下以提供合适的空气计量间隙的方式进行热生长。
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公开(公告)号：US09091175B2
公开(公告)日：2015-07-28
申请号：US13216613
申请日：2011-08-24
申请人： Eric Durocher , Maxime Demers
发明人： Eric Durocher , Maxime Demers
CPC分类号： F01D5/147 , F01D5/20 , Y10T29/49339
摘要： A stiffener rib for a non-cooled, hollow core airfoil of a turbine blade is described. The stiffener rib is constituted by an elongated solid metal piece dimensioned for securement in a hollow region of a core portion of the airfoil. The stiffener rib is shaped and oriented upwards from a leading edge of the airfoil at a predetermined calculated angle to minimize mode 2 deformation of the blade at a trailing edge thereof while improving the rigidity of the turbine blade.
摘要翻译： 描述了用于涡轮叶片的未冷却的空心芯翼型的加强肋。 加强肋由细长的固体金属片构成，其尺寸适于固定在翼型的芯部的中空区域中。 加强肋成形并且以预定的计算角度从翼型的前缘向上定向，以最小化叶片在其后缘处的模式2变形，同时提高涡轮叶片的刚度。
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公开(公告)号：US20130251508A1
公开(公告)日：2013-09-26
申请号：US13425816
申请日：2012-03-21
申请人： Marc Tardif , Sri Sreekanth , Eric Durocher
发明人： Marc Tardif , Sri Sreekanth , Eric Durocher
CPC分类号： F01D5/187 , F01D9/02 , F05D2240/81 , F05D2260/96 , Y10T29/4932
摘要： A turbine vane of a gas turbine engine is provided with a hollow core in the leading edge of the outer platform thereof. The core is interconnected with the leading edge core of the airfoil whereby to create a cooling air stream having a dual purpose and cooling both the leading edge of the outer platform and of the airfoil and thereby reducing cooling air consumption. The cooling air enters the core of the outer platform through an inlet port and exits through cooling holes provided in the leading edge of the airfoil.
摘要翻译： 燃气涡轮发动机的涡轮叶片在其外平台的前缘中设置有中空芯。 芯部与翼型件的前缘芯相互连接，从而形成具有双重目的的冷却空气流，同时冷却外部平台和翼型的前缘，从而减少冷却空气的消耗。 冷却空气通过入口进入外平台的核心，并通过设在翼型前缘的冷却孔排出。
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公开(公告)号：US08500392B2
公开(公告)日：2013-08-06
申请号：US12572104
申请日：2009-10-01
申请人： Eric Durocher , John Pietrobon
发明人： Eric Durocher , John Pietrobon
IPC分类号： F01D9/06
摘要： A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array.
摘要翻译： 设置密封壳体以基本上覆盖燃气涡轮发动机的叶片阵列管道的至少一个管道壁，并且在中涡轮机框架中采用一个示例性布置。 该装置通过设置沿管道壁延伸的多个空腔来提供叶片排放管道的改进的密封。 该布置还可以包括绝缘管，以帮助密封穿过叶片阵列的载荷传递轮辐。
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公开(公告)号：US20130111906A1
公开(公告)日：2013-05-09
申请号：US13292289
申请日：2011-11-09
申请人： RICHARD BOUCHARD , John Pietrobon , Eric Durocher
发明人： RICHARD BOUCHARD , John Pietrobon , Eric Durocher
IPC分类号： F01N13/00
摘要： A turbine exhaust case for a turbofan engine comprises a plurality of arcuate acoustic panels assembled into a circumferentially extending inner shroud with circumferential gaps between adjacent acoustic panels. An outer shroud extends circumferentially about the inner shroud. The inner shroud and the outer shroud define an annular gaspath therebetween. A plurality of circumferentially spaced-apart exhaust struts extends radially across the annular gaspath and structurally connects the individual acoustic panels forming the inner shroud to the outer shroud.
摘要翻译： 用于涡轮风扇发动机的涡轮机排气箱包括组装成周向延伸的内护罩的多个弓形声波面板，在相邻的声学面板之间具有圆周间隙。 外护罩围绕内护罩周向延伸。 内护罩和外护罩在其间限定了环形气路。 多个周向间隔开的排气支柱径向延伸穿过环形气体路径，并将构成内护罩的各个隔音板结构连接到外护罩上。
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9.发明申请公开(公告)号：US20120110849A1
公开(公告)日：2012-05-10
申请号：US13351634
申请日：2012-01-17
申请人： Eric Durocher , Anca Mateescu
发明人： Eric Durocher , Anca Mateescu
IPC分类号： B23P15/02
CPC分类号： F01D25/285 , F01D9/04 , F05D2230/60 , F05D2230/68 , Y10T29/49245 , Y10T29/49321 , Y10T29/49323 , Y10T29/53613 , Y10T29/53635
摘要： A method for assembling a vane ring with a vane support of a vane assembly in a gas turbine engine is described, and includes flexing each of the radial loading elements into the resiliently flexed state simultaneously by sliding the radial loading elements against corresponding lead-in tapers. This can be achieved, for example, using a guide tool which includes a plurality of segments bearing the lead-in tapers and which is previously assembled to the vane support.
摘要翻译： 描述了一种在燃气涡轮发动机中组装具有叶片组件的叶片支撑件的叶片环的方法，并且包括通过相对于相应的引入锥形部分滑动径向加载元件来将每个径向加载元件同时弯曲成弹性弯曲状态 。 这可以通过例如使用引导工具来实现，所述引导工具包括多个带有引入锥形部分并且预先组装到叶片支撑件的部分。
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公开(公告)号：US08166767B2
公开(公告)日：2012-05-01
申请号：US12905663
申请日：2010-10-15
申请人： Nicolas Grivas , Bhawan B. Patel , Oleg Morenko , Eric Durocher
发明人： Nicolas Grivas , Bhawan B. Patel , Oleg Morenko , Eric Durocher
CPC分类号： F01D9/023 , F01D9/042 , F01D11/005 , F05D2240/80 , F05D2250/41 , F05D2260/94 , F05D2260/941 , F23R2900/00005 , Y02T50/675
摘要： An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.
摘要翻译： 用于燃气涡轮发动机的组件包括燃烧器和设置在其下游的叶片组件。 叶片组件的外平台的一部分限定了与燃烧器的轴向滑动接头连接，并且包括位于与燃烧器相对的外周表面中的多个凹陷。 凹陷被布置在围绕外平台的圆周的期望的较高热增长的区域中，使得整个外平台的热生长在其周向基本上均匀。
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