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公开(公告)号：US07186073B2
公开(公告)日：2007-03-06
申请号：US10976525
申请日：2004-10-29
IPC分类号： F01D1/24
CPC分类号： F02C3/067 , F01D1/26 , F01D5/03 , F02K3/072 , F05D2230/60 , Y10T29/49321
摘要： A method for assembling a gas turbine engine includes providing a low-pressure turbine inner rotor that includes at least a first pair of adjacent rows of turbine blades that are configured to rotate in a first direction providing a low-pressure turbine outer rotor that includes a forward end, an aft end, and at least one row of turbine blades that is rotatably coupled between the first pair of inner rotor turbine blades, wherein the at least one row of outer rotor turbine blades is configured to rotate in a second direction that is opposite the first direction, and coupling a support assembly between the first pair of inner rotor turbine blades such that the support assembly supports the outer rotor forward end.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括提供一种低压涡轮机内转子，该低转速涡轮机内转子包括至少第一对相邻的涡轮机叶片排，其构造成沿第一方向旋转，从而提供低压涡轮机外转子，该低转速涡轮机外转子包括 前端，后端和至少一排涡轮机叶片，其可旋转地联接在第一对内转子涡轮机叶片之间，其中至少一排外转子涡轮机叶片被构造成沿着第二方向旋转， 与第一方向相反，并且将支撑组件联接在第一对内转子涡轮叶片之间，使得支撑组件支撑外转子前端。
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72.发明授权公开(公告)号：US06711887B2
公开(公告)日：2004-03-30
申请号：US10223163
申请日：2002-08-19
IPC分类号： F02C3073
CPC分类号： F02K3/072 , F01D1/26 , F02C3/067 , Y02T50/671
摘要： A low pressure turbine section for an aircraft gas turbine engine includes a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotors include low pressure first and second turbine blade rows disposed across the turbine flowpath and drivingly connected to first and second fan blade rows, respectively. The first low pressure turbine blade rows are disposed downstream of the second low pressure turbine blade rows along said low pressure turbine flowpath. Rows of non-rotatable low pressure vanes are disposed across the low pressure turbine flowpath between the first low pressure turbine blade rows and between the second low pressure turbine blade rows. An annular vaneless gap may be located between an aftmost row of the second low pressure turbine blade rows and a forwardmost row of the first low pressure turbine blade rows.
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73.发明申请公开(公告)号：US20080229751A1
公开(公告)日：2008-09-25
申请号：US11657829
申请日：2007-01-25
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。
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公开(公告)号：US07093446B2
公开(公告)日：2006-08-22
申请号：US10941508
申请日：2004-09-15
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.
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公开(公告)号：US08205458B2
公开(公告)日：2012-06-26
申请号：US11967479
申请日：2007-12-31
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。
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公开(公告)号：US07836703B2
公开(公告)日：2010-11-23
申请号：US11765522
申请日：2007-06-20
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。
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公开(公告)号：US20100047056A1
公开(公告)日：2010-02-25
申请号：US11967479
申请日：2007-12-31
IPC分类号： F02C7/12
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。
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公开(公告)号：US08104292B2
公开(公告)日：2012-01-31
申请号：US11957653
申请日：2007-12-17
IPC分类号： F03B11/00
CPC分类号： F01D9/04 , F01D5/186 , F01D5/187 , F01D25/08 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.
摘要翻译： 燃气涡轮发动机护罩包括一排不同的第一和第二护罩段，沿周向交替排列。 第一段具有延伸穿过其中的第一冷却孔的第一图案。 第二段具有延伸穿过其中的第二冷却孔的第二图案。 相应的模式具有不同的集体流量能力。
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公开(公告)号：US07739873B2
公开(公告)日：2010-06-22
申请号：US11256786
申请日：2005-10-24
申请人： Kattalaicheri Srinivasan Venkataramani , William Joseph Myers, Jr. , Robert Joseph Orlando , Paul Cooker , Ching-Pang Lee
发明人： Kattalaicheri Srinivasan Venkataramani , William Joseph Myers, Jr. , Robert Joseph Orlando , Paul Cooker , Ching-Pang Lee
IPC分类号： F02C9/00
CPC分类号： F02C9/263 , F05D2270/112 , F05D2270/3032 , F23K5/005 , F23K5/06 , F23K2203/105 , F23N1/00 , F23N1/002 , F23N5/02 , F23N5/022 , F23N5/24 , F23N5/242
摘要： A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle valves to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves may be modulating valves. The electronic controller may be used to individually control the fuel nozzle valves. The hot streak conditions may be sensed with temperature sensors such as temperature sensors operably mounted in the combustor. A program in the electronic controller may be used for determining broken or malfunctioning sensors by calculating a combustor temperature and comparing it to measured temperatures from the sensors and comparing the measured fuel pressures in the individual fuel nozzle circuits with the simulated or calculated fuel pressures.
摘要翻译： 燃气涡轮发动机燃烧系统包括多个燃料喷射器，其周向地设置在与多个燃料喷嘴阀一对一燃料供给关系中的燃烧器周围;以及电子控制器，用于控制燃料喷嘴阀以消除和/或减少热量 响应于感测到的热条件条件。 燃料喷嘴阀可以是调节阀。 电子控制器可以用于单独地控制燃料喷嘴阀。 温度传感器可以感测热条纹条件，诸如可操作地安装在燃烧器中的温度传感器。 电子控制器中的程序可用于通过计算燃烧器温度并将其与来自传感器的测量温度进行比较并将各个燃料喷嘴回路中测量的燃料压力与模拟或计算的燃料压力进行比较来确定破坏或故障的传感器。
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公开(公告)号：US20090155051A1
公开(公告)日：2009-06-18
申请号：US11957653
申请日：2007-12-17
IPC分类号： F02C7/12
CPC分类号： F01D9/04 , F01D5/186 , F01D5/187 , F01D25/08 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.
摘要翻译： 燃气涡轮发动机护罩包括一排不同的第一和第二护罩段，沿周向交替排列。 第一段具有延伸穿过其中的第一冷却孔的第一图案。 第二段具有延伸穿过其中的第二冷却孔的第二图案。 相应的模式具有不同的集体流量能力。
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