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1. 发明申请

WO2022036996A1 转子增压燃气轮机审中-公开
公开(公告)号：WO2022036996A1
公开(公告)日：2022-02-24
申请号：PCT/CN2021/000174
申请日：2021-08-18
申请人：韩培洲
发明人：韩培洲 HAN, Peizhou
IPC分类号： F02C3/04 , F02C7/00 , F02C7/04 , F02C7/045 , F01D25/30 , F02C3/16 , F02C7/22 , F01D25/24 , F23R3/42 , F02B55/02
摘要：一种转子增压燃气轮机，除在转子（41）上设置第一排的燃烧室（45）以外，还在第一排燃烧室（45）之后增设第二排及第三排燃烧室（45'，45''），相应的在转子壳（28）上也设置了与多排燃烧室（45，45'，45''）相沟通的通向涡轮（25）的相应换气输气管（17）。

2. 发明申请

WO2019104417A1 GAS TURBINE ENGINES AND COMPRESSION SYSTEMS THEREFOR 审中-公开
公开(公告)号：WO2019104417A1
公开(公告)日：2019-06-06
申请号：PCT/CA2018/051384
申请日：2018-10-31
申请人： SUNG, Rayne
发明人： SUNG, Rayne
IPC分类号： F02C3/04 , F04D19/02
摘要： A gas turbine engine, with a conical screw integrated compression system, that utilizes at least one conical screw as an intermediary fluid transport device to facilitate the multi-staging of non-axial compressors, such as centrifugal and diagonal compressors, as well as or alternatively to combine non-axial compressors to axial compressors and to the fan. The conical screw in the compression system applies axial flow translation and funnels, as necessary, the exit flow of the impeller, fan or compressor into the next impeller or compressor.

3. 发明申请

WO2018169578A2 INTERDIGITATED COUNTER ROTATING TURBINE SYSTEM AND METHOD OF OPERATION 审中-公开
公开(公告)号：WO2018169578A2
公开(公告)日：2018-09-20
申请号：PCT/US2017/065533
申请日：2017-12-11
申请人： GENERAL ELECTRIC COMPANY
发明人： STUART, Alan, Roy , CLEMENTS, Jeffrey, Donald , SCHMIDT, Richard , MONIZ, Thomas, Ory
IPC分类号： F02C3/04 , F02K3/06 , F02C7/36
摘要： The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion section, and a turbine section in serial flow arrangement. The turbine section includes, in serial flow arrangement, a first stage of a low speed turbine rotor, a high speed turbine rotor, a second stage of the low speed turbine rotor, an intermediate speed turbine rotor, and one or more additional stages of the low speed turbine rotor. The low speed turbine rotor is coupled to the fan rotor via a low pressure shaft. The intermediate speed turbine rotor is coupled to the intermediate pressure compressor via an intermediate pressure shaft. The high speed turbine rotor is coupled to the high pressure compressor via a high pressure shaft. The method includes rotating the low speed turbine rotor in a first direction along the circumferential direction; rotating the high speed turbine rotor in a second direction opposite of the first direction along the circumferential direction; and rotating the intermediate speed turbine rotor in the second direction.

4. 发明申请

WO2017093768A1 ENERGY STORAGE SYSTEM 审中-公开
标题翻译：能源储存系统
公开(公告)号：WO2017093768A1
公开(公告)日：2017-06-08
申请号：PCT/GB2016/053831
申请日：2016-12-05
申请人： CHEESECAKE ENERGY LTD.
发明人： CODD, Paul , GARVEY, Seamus , CÁRDENAS, Bruno , KANTHARAJ, Bharath , SIMPSON, Michael , PIMM, Andrew , GARVEY, James
IPC分类号： F02C6/16 , F02C3/04
CPC分类号： F02C6/16 , F02C3/04 , Y02E60/15
摘要： A system comprising two or more thermal stores, a single store for pressurised air and a means of collecting relatively low-grade heat offers the potential for an energy storage system that achieves two desirable aims at the same time: (i) the total exergy that may be released when a given pressurised air store is discharged is maximised and (ii) the ratio between the exergy extracted and the work invested in compressing the air via a multi-stage compressor is also increased by exploiting some source of low-grade heat to augment the thermal content of several thermal stores. The system comprises a compressed air energy storage system which tends, in any one fill-empty cycle of the pressurised air store, to pump heat upwards in temperature from lower-grade stores to the highest-grade thermal store as well as a thermal capture subsystem that can augment the heat content of the lower-grade thermal stores. Some provision is also present whereby other fluid can be introduced into the expansion process in addition to the air that was compressed via the multi-stage compressor facility.
摘要翻译：包括两个或更多个热储存器，用于加压空气的单个储存器和收集相对低等级热量的装置的系统提供了能量储存系统的潜力，其同时实现两个期望的目标：（i）当给定的加压空气存储排出时可能释放的总的有效能最大化并且（ii）通过多级压缩机提取的火力和投入压缩空气的工作之间的比率也通过利用一些低等级热源来增加几个热储库的热含量。该系统包括压缩空气能量存储系统，该压缩空气能量存储系统在加压空气存储的任何一个填空循环中趋向于将温度从较低等级的存储器向上泵送至最高等级的热存储以及热捕获子系统这可以增加较低等级的热存储器的热量。还有一些规定，除了通过多级压缩机设备压缩的空气外，还可以将其它流体引入膨胀过程。

5. 发明申请

WO2015191100A1 TURBO-COMPOUND REHEAT COMBINED CYCLE POWER GENERATION 审中-公开
标题翻译：涡轮复合回火组合循环发电
公开(公告)号：WO2015191100A1
公开(公告)日：2015-12-17
申请号：PCT/US2014/065694
申请日：2014-11-14
申请人： BECHTEL POWER CORPORATION
发明人： GULEN, Seyfettin, C.
IPC分类号： F01K23/14 , F01K23/10 , F02B63/04 , F02C6/00 , F02C3/04
CPC分类号： F02B73/00 , F02B41/10 , F02B63/04 , F02B63/044 , F02B75/16 , F02B77/13 , F02B2063/045 , F02C6/12 , F02G5/02 , Y02E20/14 , Y02E20/16 , Y02T10/163 , Y02T10/166
摘要： A power generation plant has two internal combustion engines (ICE) coupled in a compound configuration to operate electrical generators. A first ICE is a piston/cylinder engine producing high temperature and high pressure exhaust. The exhaust is coupled to the combustion air inlet of the second ICE, which is a gas turbine engine. A heat exchanger transfers heat from the exhaust of the first ICE to a bottoming cycle for additional power generation, also reducing the temperature at the turbine engine combustor. The second ICE (the gas turbine) is operated without an intake compressor, relying instead on the high pressure of the first ICE exhaust. The drive shaft of the gas turbine (or an associated generator/motor or a common shaft) operates a multi-stage turbo-compressor at the combustion air intake of the first ICE for improving engine power output without sapping exhaust energy as with a turbocharger.
摘要翻译：一个发电厂有两个联合在复合配置中的内燃机（ICE）来运行发电机。第一个ICE是生产高温和高压排气的活塞/气缸发动机。排气与作为燃气涡轮发动机的第二ICE的燃烧空气入口连接。热交换器将热量从第一ICE的排气转移到底循环以用于额外的发电，还降低涡轮发动机燃烧器处的温度。第二个ICE（燃气轮机）在没有进气压缩机的情况下运行，而是依赖于第一个ICE排气的高压。燃气轮机（或相关联的发电机/电动机或公共轴）的驱动轴在第一ICE的燃烧空气入口处操作多级涡轮压缩机，用于改善发动机功率输出，而不会像涡轮增压器那样排除废气能量。

6. 发明申请

WO2015088830A1 SYSTEM AND APPARATUS FOR INTERCHANGEABLE SMART GEARBOX 审中-公开
标题翻译：可交换智能齿轮箱的系统和装置
公开(公告)号：WO2015088830A1
公开(公告)日：2015-06-18
申请号：PCT/US2014/068182
申请日：2014-12-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： DUONG, Hung
IPC分类号： F02C3/04 , F02C7/22 , F02C7/26
CPC分类号： F16H57/025 , F02C7/32 , F16H1/222 , F16H57/033
摘要： Adapter plates for mounting accessories to a gearbox of a turbine engine are described herein. The adapter plates may be inverted to mount with various equipment, such as a variable frequency generator, oil pump, a fuel pump, a hydraulic pump, an alternator, an electrical generator, and a starter. Gear shafts may comprise splines in a particular form/shape for mating with the gears. The gears may be inverted to expose a desired spline configuration.
摘要翻译：这里描述了用于将配件安装到涡轮发动机的齿轮箱的适配器板。适配器板可以倒置以安装各种设备，例如变频发生器，油泵，燃料泵，液压泵，交流发电机，发电机和起动器。齿轮轴可以包括用于与齿轮配合的特定形式/形状的花键。齿轮可以被倒置以暴露期望的花键配置。

7. 发明申请

WO2015050576A1 HIGH EFFICIENCY GEARED TURBOFAN 审中-公开
标题翻译：高效齿轮涡轮机
公开(公告)号：WO2015050576A1
公开(公告)日：2015-04-09
申请号：PCT/US2014/020483
申请日：2014-03-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SCHWARZ, Frederick M. , MAGGE, Shankar S.
IPC分类号： F02K3/06 , F02C3/04
CPC分类号： F01D15/12 , F01D5/06 , F01D5/18 , F02C7/36 , F02K3/04 , F02K3/06 , F05D2220/36 , F05D2240/60 , F05D2260/4031
摘要： A gas turbine engine comprises a fan drive turbine. The fan drive turbine drives the fan through a gear reduction; A change in enthalpy is defined across the gas turbine engine. The change in enthalpy divided by a speed of the fan drive turbine squared is less than or equal to about 1.8. An axial component of gases approaching an upstream most blade of the fan drive turbine divided by the speed of the fan drive turbine is equal to or less than about 0.9.
摘要翻译：燃气涡轮发动机包括风扇驱动涡轮机。风扇驱动涡轮驱动风扇通过齿轮减速; 在燃气涡轮发动机上定义焓变化。焓的变化除以风扇驱动轮机平均速度小于或等于约1.8。接近风扇驱动涡轮机的最上游叶片的气体的轴向分量除以风扇驱动涡轮机的速度等于或小于约0.9。

8. 发明申请

WO2014183651A1 飞行器管道轮燃气发动机审中-公开
公开(公告)号：WO2014183651A1
公开(公告)日：2014-11-20
申请号：PCT/CN2014/077548
申请日：2014-05-15
申请人：林钧浩
发明人：林钧浩
IPC分类号： F02C3/04
CPC分类号： F02C3/165 , F01D1/32 , F23R3/56 , Y02T50/671
摘要：一种飞行器管道轮燃气发动机，设有旋转式的管道燃烧动力轮（17），燃烧动力轮（17）由燃烧动力轮盘（18）和火焰燃气管（20）构成，燃烧动力轮盘（18）跟转子传动轴（5）连接，火焰燃气管（20）前部沿燃烧动力轮（17）轴向由前向后顺燃烧动力轮（17）转向缠绕固定在燃烧动力轮（17）上，火焰燃气管（20）后部靠近火焰燃气管出口部位逆燃烧动力轮（17）转向弯转沿切向置于燃烧动力轮（17）上，火焰燃气管出口（22）方向跟燃烧动力轮（17）旋转切向方向相反，火焰燃气管出口（22）跟发动机排气道（3）连通，火焰燃气管进口（21）跟风管轮换向减速风管（11）连通，燃料贮存箱出料口（26）跟发动机进气道（2）连通，该飞行器管道轮燃气发动机结构简单，使用范围广，能够适应多种特殊情况使用需要。

9. 发明申请

WO2014163709A2 PLATFORM FOR CERAMIC MATRIX COMPOSITE TURBINE BLADES 审中-公开
标题翻译：陶瓷基体复合涡轮叶片平台
公开(公告)号：WO2014163709A2
公开(公告)日：2014-10-09
申请号：PCT/US2013078423
申请日：2013-12-31
申请人： USKERT RICHARD C , BASILETTI MATTHEW P , THOMAS DAVID J , FREEMAN TED J , TUCKER MICHELLE L
发明人： USKERT RICHARD C , BASILETTI MATTHEW P , THOMAS DAVID J , FREEMAN TED J , TUCKER MICHELLE L
IPC分类号： F02K3/04 , F02C3/04
CPC分类号： F01D5/3084 , F01D5/225 , F01D5/282 , F01D5/3007 , F01D5/3092 , F01D11/008 , F05D2240/55 , F05D2240/80 , F05D2260/96 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/49321
摘要： The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine blade and radial extensions to engage a portion of a root of each turbine blade. A method of making the turbine wheel is provided.
摘要翻译：本公开提供了一种涡轮机叶轮，其具有设置成将陶瓷涡轮机叶片柔性地固定到可旋转盘的叶片平台。平台包括相对的端部以接合每个涡轮机叶片的翼型件的一部分和径向延伸部以接合每个涡轮叶片的根部的一部分。提供制造涡轮机叶轮的方法。

10. 发明申请

WO2014105237A3 GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY 审中-公开
标题翻译：齿轮涡喷头初级和次级喷嘴集成几何
公开(公告)号：WO2014105237A3
公开(公告)日：2014-08-21
申请号：PCT/US2013061927
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORP
发明人： KUPRATIS DANIEL BERNARD , KOHLENBERG GREGORY A
IPC分类号： F02C9/16 , F02C3/04 , F02C7/20 , F02K3/06
CPC分类号： F02K3/075 , F01D21/045 , F02C7/32 , F02K1/04 , F05D2260/30 , F05D2260/311 , Y10T29/49245
摘要： A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.
摘要翻译：所公开的示例齿轮涡轮风扇发动机包括风扇部分，该风扇部分包括围绕轴线可旋转的多个风扇叶片和围绕发动机轴线限定的核心发动机部分。核心发动机部分包括主喷嘴，该主喷嘴包括在主喷嘴后缘处的主外径和在主后缘的前方的主最大内径。旁通通道是次级喷嘴，其包括次级喷嘴后缘处的外径和次级后缘前方的次级最大内径。主喷嘴的最大内径与主喷嘴的后缘处的外径之间的比率以及次级后缘的最大内径与次级喷嘴的后缘处的外径之间的比率都是小于约0.700。

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