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1. 发明申请

US20080229751A1 Cooling system for gas turbine engine having improved core system 审中-公开
标题翻译：具有改进的核心系统的燃气轮机的冷却系统
公开(公告)号：US20080229751A1
公开(公告)日：2008-09-25
申请号：US11657829
申请日：2007-01-25
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee
IPC分类号： F02C7/08
CPC分类号： F02K3/06 , F02C7/224 , F23D2214/00 , F23R3/28
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the booster compressor, the core system further comprising a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft; and, a system for cooling the combustion system, wherein fuel is utilized as a cooling fluid prior to being supplied to the combustion system. The core system may further include an intermediate compressor positioned downstream of and in flow communication with the compressor connected to a second drive shaft; and an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于增压压缩机下游的核心系统，所述核心系统还包括燃烧系统，用于从提供给其入口的流体流产生具有增加的压力和温度的气体脉冲，以便在出口处产生工作流体; 位于所述核心系统下游并与所述核心系统流动连通的低压涡轮机，所述低压涡轮机用于为所述第一驱动轴提供动力; 以及用于冷却燃烧系统的系统，其中燃料在被供应到燃烧系统之前用作冷却流体。核心系统可以进一步包括位于与连接到第二驱动轴的压缩机下游并与其连通的中间压缩机; 以及位于与工作流体流动连通的燃烧系统下游的中间涡轮机。

2. 发明授权

US07096674B2 High thrust gas turbine engine with improved core system 有权
标题翻译：具有改进的核心系统的高推力燃气轮机
公开(公告)号：US07096674B2
公开(公告)日：2006-08-29
申请号：US10941546
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
IPC分类号： F02C6/08
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。

3. 发明授权

US07926289B2 Dual interstage cooled engine 有权
标题翻译：双级冷却发动机
公开(公告)号：US07926289B2
公开(公告)日：2011-04-19
申请号：US11595670
申请日：2006-11-10
申请人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
发明人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F02C6/08
CPC分类号： F02C9/18 , F01D5/081 , F01D5/082 , F01D5/088 , F01D9/06 , F01D9/065 , F02C9/52 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.
摘要翻译：燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。第一级间泄放电路在压缩机的第一预热阶段和涡轮机中的中空叶片之间流动连通地连接，以向其提供加压的一次空气。第二级间泄放电路在压缩机的第二预热阶段与涡轮机叶片之间流动连通地连接，以提供比一次空气低的压力的加压次级空气。

4. 发明授权

US07510371B2 Forward tilted turbine nozzle 有权
标题翻译：前倾式涡轮喷嘴
公开(公告)号：US07510371B2
公开(公告)日：2009-03-31
申请号：US11145837
申请日：2005-06-06
申请人： Robert Joseph Orlando , Thomas Ory Moniz , Ching-Pang Lee , David Glenn Cherry , Robert John Beacock , William Larson Clifford , Scott Michael Carson
发明人： Robert Joseph Orlando , Thomas Ory Moniz , Ching-Pang Lee , David Glenn Cherry , Robert John Beacock , William Larson Clifford , Scott Michael Carson
IPC分类号： F04D29/44
CPC分类号： F01D5/141 , F01D5/142 , F01D9/041 , F02C3/067 , F02K3/072 , F05D2220/323 , F05D2250/314 , Y02T50/671 , Y02T50/673
摘要： A turbine nozzle includes a row of vanes joined to radially outwardly inclined outer and inner bands. Each vane has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges thereof. The trailing edges are tilted forwardly from the inner band to the outer band for increasing aerodynamic efficiency.
摘要翻译：涡轮喷嘴包括连接到径向向外倾斜的外带和内带的一排叶片。每个叶片具有弧度和锐角，用于在其后缘排出的燃烧气体中引入涡流。后缘从内带向外倾斜，以提高空气动力学效率。

5. 发明申请

US20080112795A1 Dual interstage cooled engine 有权
标题翻译：双级冷却发动机
公开(公告)号：US20080112795A1
公开(公告)日：2008-05-15
申请号：US11595670
申请日：2006-11-10
申请人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
发明人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F01D5/18
CPC分类号： F02C9/18 , F01D5/081 , F01D5/082 , F01D5/088 , F01D9/06 , F01D9/065 , F02C9/52 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.
摘要翻译：燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。第一级间泄放电路在压缩机的第一预热阶段和涡轮机中的中空叶片之间流动连通地连接，以向其提供加压的一次空气。第二级间泄放电路在压缩机的第二预热阶段与涡轮机叶片之间流动连通地连接，以提供比一次空气低的压力的加压次级空气。

6. 发明授权

US07093446B2 Gas turbine engine having improved core system 有权
公开(公告)号：US07093446B2
公开(公告)日：2006-08-22
申请号：US10941508
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee
IPC分类号： F02C6/08
CPC分类号： F02C5/00 , F05D2260/20 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a drive shaft; a booster compressor positioned downstream of the fan section including a plurality of stages, where each stage includes a stationary compressor blade row and a rotating compressor blade row connected to the drive shaft and interdigitated with the stationary compressor blade row; and, a combustion system for producing pulses of gas having increased pressure and temperature of a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet. A first source of compressed air from the booster compressor is provided to the combustion system inlet and a second source of compressed air from the booster compressor is provided to cool the combustion system, where the pressure of the compressed air from the second source has a greater pressure than that of the compressed air from the first source.

7. 发明授权

US08205458B2 Duplex turbine nozzle 有权
标题翻译：双相涡轮喷嘴
公开(公告)号：US08205458B2
公开(公告)日：2012-06-26
申请号：US11967479
申请日：2007-12-31
申请人： Ching-Pang Lee , Robert Joseph Orlando
发明人： Ching-Pang Lee , Robert Joseph Orlando
IPC分类号： F01D5/18
CPC分类号： F01D25/12 , F01D9/041 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A duplex turbine nozzle includes a row of different first and second vanes alternating circumferentially between radially outer and inner bands in vane doublets having axial splitlines therebetween. The vanes have opposite pressure and suction sides spaced apart in each doublet to define an inboard flow passage therebetween, and corresponding outboard flow passages between doublets. The vanes have different patterns of film cooling holes with larger cooling flow density along the outboard passages than along the inboard passages.
摘要翻译：双相涡轮喷嘴包括一排不同的第一和第二叶片，其在叶片双重体的径向外部和内部带之间周向交替，其间具有轴向分裂线。叶片具有相反的压力和吸力侧面，每个双层间隔开，以在其间限定内侧流动通道，并且在双层之间具有相应的外侧流动通道。叶片具有不同于薄膜冷却孔的图案，沿着外侧通道具有比沿内侧通道更大的冷却流动密度。

8. 发明授权

US07870743B2 Compound nozzle cooled engine 有权
标题翻译：复合喷嘴冷却发动机
公开(公告)号：US07870743B2
公开(公告)日：2011-01-18
申请号：US11595669
申请日：2006-11-10
申请人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
发明人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F02C6/08
CPC分类号： F02C7/12 , F01D5/189 , F05D2220/3212 , F05D2260/201 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.
摘要翻译：燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。涡轮机包括喷嘴，随后是一排转子叶片。第一泄放回路在压缩机的最后阶段和喷嘴的叶片中的前冷却通道之间流动连通地连接，用于在第一压力下用加压的一次空气向其中供给第一冷却孔。第二泄放回路在压缩机的中间级与喷嘴叶片中的后冷却通道之间流动连通地连接，以在小于第一压力的第二压力下用加压的二次空气供给第二冷却孔。

9. 发明授权

US07836703B2 Reciprocal cooled turbine nozzle 有权
标题翻译：往复冷却涡轮喷嘴
公开(公告)号：US07836703B2
公开(公告)日：2010-11-23
申请号：US11765522
申请日：2007-06-20
申请人： Ching-Pang Lee , Robert Joseph Orlando
发明人： Ching-Pang Lee , Robert Joseph Orlando
IPC分类号： F02C7/12
CPC分类号： F01D9/041 , F01D5/186 , F01D5/189 , F05D2260/201 , F05D2260/202 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.
摘要翻译：涡轮喷嘴包括连接到外带和内带的第一和第二叶片。叶片包括限定外侧流动通道的外侧面，其包含轴向分裂线，并且相对的内侧限定内侧流动通道而不具有轴向分裂线。两个叶片包括用于不同地冷却内侧和外侧叶片侧面的不同冷却回路。

10. 发明授权

US07743613B2 Compound turbine cooled engine 有权
标题翻译：复合涡轮冷却发动机
公开(公告)号：US07743613B2
公开(公告)日：2010-06-29
申请号：US11595668
申请日：2006-11-10
申请人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
发明人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F02C6/08
CPC分类号： F01D9/065 , F01D25/12 , F02C7/12 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.
摘要翻译：燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。涡轮机包括一排喷嘴叶片，随后是一排转子叶片。叶片和叶片具有相应的前后冷却通道。第一，第二，第三和第四泄放回路与压缩机的不同级联流动连通，以在不同压力下从其中排出加压空气，以向涡轮机叶片和叶片的前后通道提供冷却剂。

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