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171. 发明授权

US4148185A Double reheat hydrogen/oxygen combustion turbine system 失效
标题翻译：双重再热氢/氧燃气轮机系统
公开(公告)号：US4148185A
公开(公告)日：1979-04-10
申请号：US824591
申请日：1977-08-15
申请人： Edward V. Somers
发明人： Edward V. Somers
IPC分类号： F01K25/00 , F02C3/22 , F02C6/00 , F02C7/141 , F02C3/18
CPC分类号： F01K25/005 , F02C3/22 , F02C6/003 , F02C7/141
摘要： A gas turbine power generating system comprising, in the preferred embodiment, three gas turbine engines in series-connected flow communication employing high pressure hydrogen and oxygen as the fuel. Pre-heated pressurized steam (or a steam and water mixture) is fed to the initial gas turbine combustor for combustion coolant. Steam, consisting of the products of combustion plus the vaporized coolant, is exhausted from the first turbine into the combustor of the next turbine for re-heating via the combustion therein of the high pressure hydrogen and oxygen. The exhaust steam from the intermediate turbine is in turn re-heated in the combustor of the final turbine. The final exhaust steam is then passed through a recuperative heat exchanger to pre-heat the pressurized cooling water so that, when injected into the first combustor, it is vaporized prior to entering the first turbine.
摘要翻译：一种燃气轮机发电系统，在优选实施例中，包括使用高压氢气和氧气作为燃料的串联连接流动连通的三个燃气涡轮发动机。将预加热的加压蒸汽（或蒸汽和水混合物）供给到用于燃烧冷却剂的初始燃气轮机燃烧器。由燃烧产物和蒸发的冷却剂组成的蒸汽从第一涡轮机排出到下一个涡轮的燃烧器中，用于通过其中的高压氢气和氧气的燃烧进行再加热。来自中间涡轮机的排气又在最终涡轮机的燃烧器中重新加热。然后将最终排气蒸汽通过再热式热交换器以预加热加压的冷却水，使得当注入第一燃烧器时，其在进入第一涡轮机之前被蒸发。

172. 发明授权

US3623317A Gas turbine for low heating value gas 失效
标题翻译：用于低加热气体的气体涡轮机
公开(公告)号：US3623317A
公开(公告)日：1971-11-30
申请号：US3623317D
申请日：1970-06-30
申请人： STRUTHERS ENERGY SYSTEMS INC
发明人： FOSTER-PEGG RICHARD W
IPC分类号： F02C3/22 , F02C3/06
CPC分类号： F02C3/22
摘要： A GAS TURBINE HAS A COMPRESSOR, A COMBUSTION CHAMBER, AND A TURBINE WHICH DRIVES THE COMPRESSOR AND PROVIDES ADDITIONAL SHAFT WORK, AIR AND LOW HEATING VALVE GAS BEING INTRODUCED A GIVEN CIRCUMFERENTIALLY DISPOSED LOCATIONS AT THE COMPRESSOR INTAKE AND BEING WITHDRAWN AT CORRESPONDING CIRCUMFRENTIALLY DISPOSED LOCATIONS AT THE COMPRESSOR EXHAUST, ONE OF SAID LOCATIONS AT THE COMPRESSOR EXHAUST PROVIDING FUEL RICH AIR INTRODUCED INTO AND BURNED IN THE COMBUSTION CHAMBER WITH ADDITIONAL AIR FROM THE COMPRESSOR INTRODUCED THEREAFTER, PRODUCTS OF COMBUSTION FROM THE COMBUSTION CHAMBER DRIVING SAID TURBINE.

173. 发明授权

US2984978A Fuel system for supplying gaseous fuel to internal combustion engines 失效
标题翻译：用于向内燃机供应气体燃料的燃料系统
公开(公告)号：US2984978A
公开(公告)日：1961-05-23
申请号：US69273957
申请日：1957-10-28
申请人： ROLLS ROYCE
发明人： ARNOLD GRIFFITH ALAN
IPC分类号： F02C3/22 , F02C3/24 , F02C7/224
CPC分类号： F02C3/22 , F02C3/24 , F02C7/224

174. 发明授权

US2793497A Working pressure fluid generating apparatus 失效
标题翻译：工作压力液体发生装置
公开(公告)号：US2793497A
公开(公告)日：1957-05-28
申请号：US35907753
申请日：1953-06-02
申请人： WORTHINGTON CORP
发明人： HELLMUTH WALTER
IPC分类号： F02C3/22 , F02K99/00
CPC分类号： F02C3/22

175. 发明授权

US2599480A Gas turbine power plant having auxiliary turbine driven by fuel gas being supplied to the combustion chamber 失效
标题翻译：具有由燃料气体驱动的辅助涡轮机的燃气轮机发电厂被供给到燃烧室
公开(公告)号：US2599480A
公开(公告)日：1952-06-03
申请号：US73901747
申请日：1947-04-02
申请人： BBC BROWN BOVERI & CIE
发明人： HANS PFENNINGER
IPC分类号： F02C3/22
CPC分类号： F02C3/22

176. 发明授权

US2539744A Plant for the production of compressed air 失效
标题翻译：生产压缩空气的厂房
公开(公告)号：US2539744A
公开(公告)日：1951-01-30
申请号：US60967945
申请日：1945-08-08
申请人： TECH STUDIEN AG
发明人： CURT KELLER
IPC分类号： F02C3/22
CPC分类号： F02C3/22

177. 发明授权

US2305785A Working process and mechanical equipment for gas turbines 失效
标题翻译：燃气轮机的工作过程和机械设备
公开(公告)号：US2305785A
公开(公告)日：1942-12-22
申请号：US20855638
申请日：1938-05-18
申请人： GEORGE JENDRASSIK
发明人： GEORGE JENDRASSIK
IPC分类号： F02C3/16 , F02C3/22 , F02C3/26 , F02C3/36
CPC分类号： F02C3/26 , F02C3/16 , F02C3/22 , F02C3/36

178. 发明公开

US20240360791A1 CRYO-ASSISTED BOTTOMING CYCLE HEAT SOURCE SEQUENCING 审中-公开
公开(公告)号：US20240360791A1
公开(公告)日：2024-10-31
申请号：US18770803
申请日：2024-07-12
申请人： RTX CORPORATION
发明人： Brandon M. Evans , Neil J. Terwilliger
IPC分类号： F02C7/141 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/32
CPC分类号： F02C7/141 , F02C1/10 , F02C3/22 , F02C6/18 , F02C7/32 , F05D2220/323 , F05D2260/213
摘要： An aircraft propulsion system includes a bottoming cycle where a working fluid is circulated within a closed circuit that includes a bottoming compressor section and a bottoming turbine section. A first heat exchanger provides for thermal energy from a first heat source to be input into the working fluid of the bottoming cycle. A second heat exchanger that is downstream from the first heat exchanger communicates additional thermal energy from a second heat source into the working fluid of the bottoming cycle after the thermal energy from the first heat source is input into the working fluid.

179. 发明授权

US12092032B1 Gas turbine engine hydrogen supply system and method 有权
公开(公告)号：US12092032B1
公开(公告)日：2024-09-17
申请号：US18329041
申请日：2023-06-05
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Rodolphe Dudebout
IPC分类号： F02C7/224 , F02C3/22 , F02C7/232
CPC分类号： F02C7/224 , F02C3/22 , F02C7/232 , F05D2240/36 , F05D2260/213 , F05D2260/606
摘要： A system and method for supplying hydrogen to a combustor of a gas turbine engine includes supplying liquid hydrogen from a liquid hydrogen supply source to a hydrogen supply line that is adapted to be coupled to the combustor of the gas turbine engine. The liquid hydrogen is converted to gaseous hydrogen at a first pressure and is to a pump, which increases the pressure of the gaseous hydrogen to a second pressure. A flowrate of the gaseous hydrogen discharged from the pump is controlled using a fuel metering valve. A portion of the gaseous hydrogen discharged from the pump is received and stored in a high-pressure gaseous hydrogen tank, and a pressure-regulating valve maintains the second pressure at a substantially constant pressure magnitude.

180. 发明授权

US12092022B2 Forward mounted hydrogen steam injected and inter-cooled turbine engine with octopus ducting 有权
公开(公告)号：US12092022B2
公开(公告)日：2024-09-17
申请号：US18106161
申请日：2023-02-06
申请人： Raytheon Technologies Corporation
发明人： Jon Erik Sobanski , Jacob C. Snyder
IPC分类号： F02C3/30 , F02C3/22
CPC分类号： F02C3/30 , F02C3/22 , F05D2260/211
摘要： A propulsion system for an aircraft includes a core engine that generates a core gas flow, a propulsor section that is driven by the core engine and disposed aft of the core engine, a nacelle that surrounds the core engine and the propulsor section, a water recovery system that is disposed in the nacelle, an exhaust duct where the core gas flow is directed radially outward from the core engine to the nacelle, an evaporator assembly that is in thermal communication with the exhaust duct where water is recovered by the water recovery system and is heated to generate a steam flow that is subsequently communicated to the core engine.

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