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公开(公告)号：EP2825760B1
公开(公告)日：2017-11-22
申请号：EP13760947.5
申请日：2013-01-24
CPC分类号： F02C3/04 , F02C3/13 , F02C6/00 , F02C6/02 , F02C9/18 , F02K3/12 , F05D2250/30 , F05D2250/311 , F05D2270/07
摘要： A gas turbine engine system includes a fan section, a low pressure compressor section downstream of the fan section, a first engine core downstream from the low pressure compressor section, a second engine core downstream from the low pressure compressor section, and a flowpath control mechanism configured to selectively restrict fluid flow through the second engine core. The first engine core includes a first engine core compressor section, a first engine core combustor downstream of the first engine core compressor section, and a first engine core turbine section downstream of the first engine core combustor. The second engine core includes a second engine core compressor section, a second engine core combustor downstream of the second engine core compressor section, and a second engine core turbine section downstream of the second engine core combustor.
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公开(公告)号：EP3108119A2
公开(公告)日：2016-12-28
申请号：EP15793193.2
申请日：2015-02-12
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F04D29/384 , F01D5/141 , F01D9/041 , F02C3/04 , F02K3/12 , F04D29/324 , F04D29/325 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2240/121 , F05D2240/303 , F05D2240/35 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
摘要翻译： 涡轮发动机的翼型件包括压力侧和吸力侧，所述压力侧和吸力侧在从0％跨度位置到100％跨距位置的径向方向上延伸。 翼型在前缘角度和跨度位置之间具有关系，该关系定义了具有从80％跨度到100％跨度的递减负斜率或正斜率中的至少一个的曲线。
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公开(公告)号：EP2587039A3
公开(公告)日：2016-11-09
申请号：EP12189326.7
申请日：2012-10-19
发明人： Kupratis, Daniel B.
摘要： A method of operating a propulsion system (14) includes powering an auxiliary fan (18) with a gas turbine engine (20), where the auxiliary fan (18) is along an auxiliary axis (F) and the gas turbine engine (20) is along an engine axis (F), the auxiliary axis (F) being parallel to the engine axis (A).
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5.发明授权
公开(公告)号：EP2518293B1
公开(公告)日：2016-09-28
申请号：EP12165824.9
申请日：2012-04-26
发明人： Norris, James W.
CPC分类号： F02K3/12 , F02C3/145 , F02C9/18 , F02K3/06 , F02K3/077 , F05D2230/52 , F05D2240/40 , F05D2250/314 , Y02T50/671
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公开(公告)号：EP1574689B1
公开(公告)日：2013-12-04
申请号：EP05251403.1
申请日：2005-03-08
CPC分类号： F02C6/08 , F01D13/003 , F01D13/02 , F02C6/06 , F02K3/06 , F02K3/12 , F05D2220/50
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7.发明公开Dispositif de propulsion à cycle variable par prélèvement d'air comprimé pour avion supersonique 有权Schubvorrichtung mit variablen Betriebszyklen mit aufgeteilter VerdichterluftfürÜberschallflugzeuge
公开(公告)号：EP1267062A1
公开(公告)日：2002-12-18
申请号：EP02291358.6
申请日：2002-06-04
申请人： SNECMA MOTEURS
发明人： Franchet, Michel , Laugier, Yann , Loisy, Jean
CPC分类号： F02K3/025 , F02K3/075 , F02K3/12 , Y02T50/671
摘要： Dispositif de propulsion à cycle variable pour avion supersonique comprenant au moins un propulseur (1) ayant au moins un compresseur et capable de générer une poussée pour les vitesses de vol supersonique, au moins un ensemble propulsif auxiliaire (12), distinct du propulseur, capable de générer un complément de poussée pour le décollage, l'atterrissage et les vitesses de vol subsonique, au moins une conduite (20) reliant le propulseur (1) à l'ensemble propulsif auxiliaire (12) pour acheminer à ce dernier de l'air comprimé produit par le compresseur afin que l'ensemble propulsif auxiliaire génère un complément de poussée pour le décollage, l'atterrissage et le vol en croisière subsonique, et au moins une vanne permettant d'obturer la conduite pour le vol en croisière supersonique.
摘要翻译： 可变循环推进单元具有带有压缩机的推进器（1）和产生互补推力的辅助推进组件（12）。 互补单元具有从主推进器提供附加推力的推进继电器管（20）。 有一个叶片封闭了亚音速飞行的管子。
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公开(公告)号：EP2820278B1
公开(公告)日：2017-12-06
申请号：EP12869761.2
申请日：2012-12-21
发明人： KUPRATIS, Daniel, B.
摘要： A gas turbine engine has, in at least a first mode of operation, a core engine, a fan, and an auxiliary turbine engine coupled as follows. The core engine has, along a core flowpath, at least one compressor section, a combustor, and at least one turbine section. The fan is upstream of the core flowpath and drives air downstream along the core flowpath and along a bypass flowpath. The auxiliary turbine engine has an axial compressor, a fan, a combustor, and an axial turbine. The fan has fan blades and a continuation of the bypass flowpath extends sequentially downstream through the axial compressor and radially outward through passageways in the blades of the fan and a continuation of the core flowpath passes axially through the fan. The combustor is downstream of the fan along the continuation of the bypass flowpath. The axial turbine is downstream of the combustor along the continuation of the bypass flowpath and comprises at least one stage of blades rotating with the fan.
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10.发明公开SYSTEM, METHOD AND APPARATUS FOR LEAN COMBUSTION WITH PLASMA FROM AN ELECTRICAL ARC 审中-公开系统，方法和装置由圆弧与血浆稀薄燃烧
公开(公告)号：EP2255081A4
公开(公告)日：2014-02-19
申请号：EP09710927
申请日：2009-02-12
发明人： FORET TODD
CPC分类号： F02K3/12 , B64G1/405 , B64G1/406 , F01D13/00 , F02C3/14 , F02C7/266 , F02K9/425 , F23R3/007 , F23R3/58 , F23R2900/00002 , F23R2900/00009 , G21D5/02 , H05H1/24 , H05H1/32 , H05H1/48 , H05H2001/4695 , Y02E50/12 , Y02T50/678
摘要： The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, (b) extends into the cylindrical vessel, and (c) can be moved along the longitudinal axis, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle creates a plasma that discharges through the hollow electrode nozzle.
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