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1. 发明授权

US12031481B2 Air bottoming cycle air cycle system source 有权
公开(公告)号：US12031481B2
公开(公告)日：2024-07-09
申请号：US18459716
申请日：2023-09-01
申请人： RTX CORPORATION
发明人： Alan Retersdorf , Stephen H. Taylor , Oliver V. Atassi
IPC分类号： F02C6/18 , F02C7/32 , F02C9/18
CPC分类号： F02C6/18 , F02C7/32 , F02C9/18 , F05D2220/62 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

2. 发明申请

US20170283021A1 MODIFIED CO2 CYCLE FOR LONG ENDURANCE UNMANNED UNDERWATER VEHICLES AND RESULTANT CHIRP ACOUSTIC CAPABILITY 审中-公开
公开(公告)号：US20170283021A1
公开(公告)日：2017-10-05
申请号：US15091415
申请日：2016-04-05
申请人： Raytheon Company
发明人： Gregory W. Heinen
IPC分类号： B63G8/08 , F01D25/14 , B63G8/00 , F01K15/04 , F01K13/02 , F01D15/04 , F01K25/08
CPC分类号： B63G8/08 , B63B2209/00 , B63G8/001 , B63G2008/002 , F01D15/045 , F01D25/145 , F01K1/12 , F01K13/02 , F01K15/04 , F01K15/045 , F01K25/08 , F01K25/103 , F05D2210/12 , F05D2220/31 , F05D2220/76 , F05D2260/10 , F05D2260/231 , F05D2260/42 , F05D2270/05
摘要： A carbon dioxide cycle power generation system includes storage collectively storing portions of carbon dioxide liquid and gas and a transfer connection selectively directing flow of the carbon dioxide through a turbine. The system cycles between different seawater depths in order to employ at least one of seawater pressure and seawater temperature in creating the carbon dioxide flow. Inlet/outlet control valves on variable volume tanks, positioned below movable pistons within the respective tank, selectively allow seawater into or out of a lower portion of the respective tank below the piston to pressurize the carbon dioxide therein relative to the carbon dioxide within the other tank when at depth rather than near the surface. Inhibited versus uninhibited heat transfer between storage portions and the seawater allows different seawater temperatures at depth and near the surface to create the carbon dioxide flow. Acoustic communications may be driven concurrent with the turbine.

3. 发明申请

US20120125290A1 HYDROGENE ENGINE 审中-公开
标题翻译：氢发动机
公开(公告)号：US20120125290A1
公开(公告)日：2012-05-24
申请号：US13302230
申请日：2011-11-22
申请人： Manfred Moder
发明人： Manfred Moder
IPC分类号： F02B5/00 , C25B9/00
CPC分类号： F01D1/32 , F02C3/165 , F02C5/04 , F02K7/005 , F02M25/12 , F05D2240/242 , F05D2260/10 , Y02T10/121
摘要： An internal combustion engine for converting energy released during the combustion of a fuel, in particular an H2-02 mixture, into mechanical work. The internal combustion engine includes at least one drive shaft connected to at least one chamber component that has at least one explosion chamber, at least one fuel supply for introducing fuel into the explosion chamber, and at least one ignition device for igniting fuel so introduced, The engine provides a relatively high torque at low engine speeds if the explosion chamber has at least one outlet through which ignited fuel is released to the surroundings, wherein the outlet is arranged such that the reaction generated by the escape of the ignited fuel exerts a torque on the at least one chamber component.
摘要翻译：用于将在燃料燃烧期间释放的能量，特别是H2-02混合物转化为机械作业的内燃机。所述内燃机包括至少一个驱动轴，所述至少一个驱动轴连接到至少一个室部件，所述至少一个室部件具有至少一个爆炸室，用于将燃料引入所述爆炸室中的至少一个燃料供应器，以及用于点燃所引入的燃料的至少一个点火装置，如果爆炸室具有至少一个出口，点燃的燃料通过该出口被释放到周围，发动机在低发动机速度下提供相对较高的扭矩，其中出口布置成使得由点燃燃料逸出产生的反作用力在所述至少一个室部件上。

4. 发明授权

US07762085B2 Turbine engine having two off-axis spools with valving-enabled modulation between high and low power modes 有权
标题翻译：涡轮发动机具有两个离轴线轴，在高功率和低功率模式之间具有启用调压功能
公开(公告)号：US07762085B2
公开(公告)日：2010-07-27
申请号：US11505519
申请日：2006-08-17
申请人： John T. Exley , George Minkkinen , Donald Hulbert , Michael D. Rudy
发明人： John T. Exley , George Minkkinen , Donald Hulbert , Michael D. Rudy
IPC分类号： F02C3/10
CPC分类号： F02C3/10 , B64C27/82 , B64C2027/8236 , F02C3/13 , F05D2220/329 , F05D2220/90 , F05D2250/313 , F05D2250/314 , F05D2260/10 , F05D2260/211 , F05D2270/053 , Y02T50/675
摘要： A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high pressure (HP) spool—where the LP spool is independently mounted remote to the HP spool. The engine may be modulated for operation by a modulation diverter valve assembly and through the fuel flow to the engine. The power output from the engine can be modulated from high levels to low levels and vice versa through control of the air flow through the engine using the modulation diverter valve assembly. In lift mode operation both the LP and HP spools may be operational, while during the forward flight cruise mode of operation the HP spool is operational and the LP spool may or may not be operational depending upon the power required for the flight condition. For HP spool only operation, the LP spool may be shut down using the modulation diverter valve assembly and an inlet flow diverter valve assembly. The convertible configuration may be achieved by the diverter valving-enabled modulation of the engine airflow direction to produce a characteristic for one embodiment having shaft power output for the vertical lift mode to propulsive thrust output for forward flight mode.
摘要翻译：公开了一种特别适用于VTOL飞机的涡轮发动机。根据各种实施例，涡轮发动机的内核包括两个阀芯 - 低压（LP）阀芯和高压（HP）阀芯，其中LP阀芯独立地安装在HP阀芯上。发动机可以通过调制转向阀组件进行调节，并通过燃油流向发动机。来自发动机的功率输出可以通过使用调制分流阀组件控制通过发动机的气流，从高电平调制到低电平，反之亦然。在提升模式操作中，LP和HP阀芯都可以运行，而在正向飞行巡航操作模式期间，HP阀芯可操作，并且LP阀芯可能或可能不会运行，具体取决于飞行条件所需的功率。对于仅HP阀芯操作，LP阀芯可能会使用调压分流阀组件和入口流量分流阀组件关闭。可转换配置可以通过发动机气流方向的转向阀启用调节来实现，以产生一个实施例的特征，该实施例具有用于垂直提升模式的轴功率输出用于向前飞行模式的推进推力输出。

5. 发明授权

US07618825B2 Method for influencing and monitoring the oxide layer on metallic components of hot CO2/H20 cycle systems 有权
标题翻译：影响和监测热CO2 / H20循环系统金属部件氧化层的方法
公开(公告)号：US07618825B2
公开(公告)日：2009-11-17
申请号：US11033166
申请日：2005-01-12
申请人： Werner Balbach
发明人： Werner Balbach
IPC分类号： G01N21/72
CPC分类号： F02C3/20 , F01D21/10 , F01D25/007 , F02C1/10 , F02C7/30 , F05D2210/12 , F05D2260/10 , F05D2260/80
摘要： A method for influencing and monitoring the oxide layer on metallic components of hot CO2/H2O cycle systems, in particular of CO2/H2O gas turbine installations, in which a hydrocarbon-containing fuel is burnt with oxygen, and the excess CO2 and H2O formed is removed from the cycle system at a suitable location. To protect the oxide layer of the components which are under thermal load, an excess of oxygen is used, the level of which is dependent on the current state of the oxide layer, the state of the oxide layer being determined by periodic and/or continuous measurements.
摘要翻译：一种影响和监测热二氧化碳/水循环系统的金属组分，特别是CO2 / H2O燃气轮机装置的氧化物层的方法，其中含烃燃料用氧气燃烧，并且形成的过量CO 2和H 2 O是在适当的位置从循环系统中移除。为了保护热负荷下的组分的氧化物层，使用过量的氧，其水平取决于氧化物层的当前状态，氧化物层的状态由周期性和/或连续性决定测量。

6. 发明授权

US07104070B2 Liquid fuel nozzle apparatus with passive water injection purge 失效
标题翻译：带有被动注水清洗的液体燃料喷嘴装置
公开(公告)号：US07104070B2
公开(公告)日：2006-09-12
申请号：US10708455
申请日：2004-03-04
申请人： Robert J. Iasillo , Warren James Mick
发明人： Robert J. Iasillo , Warren James Mick
IPC分类号： F02C3/30 , F02C7/22
CPC分类号： F02C3/22 , F02C3/24 , F02C3/30 , F02C7/22 , F05D2260/10 , F23D11/106 , F23D2206/10 , F23D2209/30 , F23L7/002 , F23R3/28
摘要： In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.
摘要翻译：在具有压缩机，燃烧器和涡轮机的燃气涡轮机中，连接以向燃烧器提供气体燃料的气体燃料供应，液体燃料供应源，其通过喷嘴组件向燃烧器提供液体燃料。喷嘴组件包括用于使流体流入燃烧器的多个通道，其中一个通道是雾化空气通道导管，其将雾化空气通道与多个通道中的一个通道相互连接，以使流体在其间流动，同时不允许流体返回雾化空气通道。来自雾化空气通道的高压空气经由管道被转移到多个通道中的一个，以保护喷嘴免受热燃烧器气体的摄入，从而消除了对于多个通道中的一个通道的专用空气净化系统的需要。

7. 发明授权

US11773778B1 Air bottoming cycle air cycle system source 有权
公开(公告)号：US11773778B1
公开(公告)日：2023-10-03
申请号：US17951936
申请日：2022-09-23
申请人： RAYTHEON TECHNOLOGIES CORPORATION
发明人： Alan Retersdorf , Stephen H. Taylor , Oliver V. Atassi
IPC分类号： F02C6/18 , F02C7/32 , F02C9/18
CPC分类号： F02C6/18 , F02C7/32 , F02C9/18 , F05D2220/62 , F05D2260/10 , F05D2260/213 , F05D2260/232
摘要： A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger and expanded through a power turbine that is coupled to drive the auxiliary compressor section.

8. 发明授权

US06966189B2 System for sealing the secondary flow at the inlet to a nozzle of a turbomachine having a post-combustion chamber 有权
标题翻译：用于将具有后燃烧室的涡轮机的喷嘴的入口处的二次流密封的系统
公开(公告)号：US06966189B2
公开(公告)日：2005-11-22
申请号：US10847864
申请日：2004-05-19
申请人： Guy Lapergue , Guillaume Sevi , Jacques Roche
发明人： Guy Lapergue , Guillaume Sevi , Jacques Roche
IPC分类号： F02C7/28 , F02C7/12 , F02C7/18 , F02C7/24 , F02K1/80 , F02K1/82 , F16J15/08 , F02K1/12
CPC分类号： F02K1/805 , F02K1/822 , F05D2260/10 , F16J15/0887 , Y02T50/675
摘要： A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle comprising a plurality of flaps hinged to the upstream end of said casing, each flap fitted on its inside face with a thermal protection plate to define a passage for cooling air delivered by said diaphragm, wherein the cooling air is provided by an annular duct defined by a first flexible annular gasket in sliding contact against the downstream inside face of the casing and against the upstream inside faces of the flaps under the pressure of the secondary flow, and defined on the inside by a second flexible annular gasket whose upstream end is fixed to the radially inner zone of the diaphragm, and whose downstream end is in sliding contact against the upstream inside face of the protection plates.
摘要翻译：一种涡轮机，包括在涡轮下游的由燃烧室内限定的用于二次流的环形通道限定的后燃烧室，固定在所述通道的下游端的环形隔膜，所述喷嘴包括多个翼片铰接到所述壳体的上游端，每个翼片在其内表面上安装有热保护板，以限定用于冷却由所述隔膜输送的空气的通道，其中所述冷却空气由第一柔性环形衬垫与壳体的下游内表面滑动接触，并且在二次流动的压力下抵靠翼片的上游内表面，并且通过第二柔性环形垫圈限定在内侧，第二柔性环形垫圈的上游端固定到径向内部区域并且其下游端与保护板的上游内表面滑动接触。

9. 发明申请

US20050193740A1 Stratojet - system and method for automatically maintaining optimum oxygen content in high altitude turbojet engines 审中-公开
标题翻译： Stratojet - 用于在高空涡轮喷气发动机中自动维持最佳氧气含量的系统和方法
公开(公告)号：US20050193740A1
公开(公告)日：2005-09-08
申请号：US10793624
申请日：2004-03-05
申请人： Adolph Mondry
发明人： Adolph Mondry
IPC分类号： F02C9/00
CPC分类号： F02C3/22 , F05D2220/32 , F05D2260/10
摘要： The Stratojet is a method and apparatus for maintaining a desired oxygen content level at the outlet of a turbojet engine to increase speed, altitude, and thrust, and to decrease flameouts and includes delivering a second liquid oxidant dosage to the duct upstream of the compressor while repeatedly sequencing through the plurality of sequential oxygen content doses at the outlet beginning with the first oxygen content dose and proceeding to an adjacent oxygen content dose in the sequence after a predetermined time interval has elapsed. The second oxidant dosage is delivered until the oxygen content level attains the desirable range, at which point corresponding oxidant and oxygen content doses are selected from the plurality of sequential oxidant doses and oxygen content doses. The method also includes delivering the selected oxidant dose and oxygen content dose so as to maintain the desired oxygen content range at the outlet.
摘要翻译： Stratojet是用于在涡轮喷气发动机的出口处保持期望的氧含量水平以提高速度，高度和推力并减少熄火并且包括将第二液体氧化剂剂量输送到压缩机上游的管道的方法和装置，同时通过从第一氧含量剂量开始的出口处的多个顺序氧含量剂量重复测序，并且在经过预定时间间隔之后继续进行到序列中相邻的氧含量剂量。递送第二氧化剂剂量直到氧含量达到所需的范围，此时相应的氧化剂和氧含量剂量选自多个顺序氧化剂剂量和氧含量剂量。该方法还包括递送所选择的氧化剂剂量和氧含量剂量，以便在出口处保持所需的氧含量范围。

10. 发明申请

US20050191755A1 Method for influencing and monitoring the oxide layer on metallic components of hot CO2/H20 cycle systems 有权
标题翻译：影响和监测热CO2 / H20循环系统金属部件氧化层的方法
公开(公告)号：US20050191755A1
公开(公告)日：2005-09-01
申请号：US11033166
申请日：2005-01-12
申请人： Werner Balbach
发明人： Werner Balbach
IPC分类号： F01D21/10 , F01D25/00 , F02C1/10 , F02C3/20 , F02C7/30 , G01N21/72
CPC分类号： F02C3/20 , F01D21/10 , F01D25/007 , F02C1/10 , F02C7/30 , F05D2210/12 , F05D2260/10 , F05D2260/80
摘要： A method for influencing and monitoring the oxide layer on metallic components of hot CO2/H2O cycle systems, in particular of CO2/H2O gas turbine installations, in which a hydrocarbon-containing fuel is burnt with oxygen, and the excess CO2 and H2O formed is removed from the cycle system at a suitable location. To protect the oxide layer of the components which are under thermal load, an excess of oxygen is used, the level of which is dependent on the current state of the oxide layer, the state of the oxide layer being determined by periodic and/or continuous measurements.
摘要翻译：一种用于影响和监测热CO 2 / H 2 O 2循环系统的金属组分上的氧化物层的方法，特别是CO 2 / H 2燃气轮机装置，其中含烃燃料被氧气燃烧，并形成过量的CO 2 H 2和H 2 O 2 在合适的位置从循环系统中移除。为了保护热负荷下的组分的氧化物层，使用过量的氧，其水平取决于氧化物层的当前状态，氧化物层的状态由周期性和/或连续性决定测量。

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