专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US12060827B2 Advanced 2-spool turboprop engine 有权
公开(公告)号：US12060827B2
公开(公告)日：2024-08-13
申请号：US18452214
申请日：2023-08-18
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F02C3/10 , F02C7/32 , F02C7/36
CPC分类号： F02C3/103 , F02C7/32 , F02C7/36 , F05D2220/323
摘要： A low cost, high power density, low emissions general aviation turbine engine (GATE) with improved fuel economy over current engines. Ideally suited for 50 to 500 shaft horsepower (SHP) range aircraft applications such as GA, UAS, UAS, air taxi, helicopters and commercial markets. The engine design features with centrifugal compressor and radial turbine rotors has a high-end practical limit of ˜800 (SHP). The new turboprop incorporates 2 non-concentric spools aero-thermal-pressure coupled wherein staged compressor rotors lend to a simple engine design, optimized high overall engine pressure ratio (OPR) and low specific fuel consumption (SFC). An integral starter—generator system further simplifies the engine design and offers high electrical output power capability for auxiliary power requirements. A 2-stage low emissions combustor with fuel-air premix chambers is incorporated lending to stable combustion at any engine spool speed/power requirement, further fuel optimization and use of a low cost simple fixed pitch propeller. Some other highlights include: any fuel or mixture thereof, TBO greater than piston or other turbine engines, less maintenance costs, oil/filter change at ˜15000 hrs. and other inherent advantages of a gas turbine engine.
Of the two spools that make up this turboprop engine, one is the High Pressure (HP) spool that is part of the gas generator using combustor hot gases to power the integral HP turbine rotor, HP compressor and high-speed alternator starter—generator. The other engine spool is the Low-Pressure (LP) spool that receives the HP turbine exhaust heat energy to power the integral LP compressor rotor, LP turbine rotor, integrated gearbox with resultant output shaft horsepower.
This invention represents the most advanced engine for general aviation since Charles Edward Taylor's engine powered the Wright Brothers first aircraft-controlled powered flight Dec. 17, 1903.

2. 发明授权

US08552575B2 Hybrid electric power for vehicular propulsion 失效
标题翻译：混合动力用于车辆推进
公开(公告)号：US08552575B2
公开(公告)日：2013-10-08
申请号：US13506179
申请日：2012-04-02
申请人： Joseph Michael Teets , Jon William Teets
发明人： Joseph Michael Teets , Jon William Teets
IPC分类号： H02P9/04
CPC分类号： G08G1/0129 , G08G1/012 , G08G1/0145
摘要： This invention relates to a hybrid gas turbine (HGT) engine powerplant having electrical output power and as a system independently or in combination with electrical energy storage means, supplies electrical power to at least one electric motor for vehicular propulsion.The HGT has a minimum of two spools at least one spool, the power spool, has integrated a compressor rotor, turbine rotor and alternator rotor; a minimum second spool for staged engine air compression has integrated a compressor and turbine rotors aero-coupled to the power spool.An electronic engine unit (EECU) supplies electrical power to the fuel control valve, has preprogrammed variable power spool speeds per output power requirements, exhaust gas turbine temperature limits for fuel economy considerations and is responsive thru vehicle throttle commands of accel, decel, constant vehicle operations, start-up, shut down, battery charger and auxiliary power applications (APU).
摘要翻译：本发明涉及一种混合燃气轮机（HGT）发动机动力装置，其具有电力输出功率和独立的系统，或与电能存储装置组合，将电力供应给用于车辆推进的至少一个电动马达。 HGT至少有两个阀芯，至少一个阀芯，动力阀芯，集成了压缩机转子，涡轮转子和交流发电机转子; 用于分级发动机空气压缩的最小第二阀芯已经将压缩机和涡轮转子集成到气动联接到动力轴。电子发动机单元（EECU）向燃料控制阀提供电力，根据每个输出功率要求预编程可变动力油卷速度，燃油经济性考虑的排气涡轮机温度限制，并且通过加速，减速，恒定车辆的车辆节气门指令来响应操作，启动，关闭，电池充电器和辅助电源应用（APU）。

3. 发明授权

US07574853B2 Microturbine with CHP system having a distillation apparatus 失效
标题翻译：具有CHP系统的微型涡轮机具有蒸馏装置
公开(公告)号：US07574853B2
公开(公告)日：2009-08-18
申请号：US11517707
申请日：2006-09-08
申请人： Joseph Michael Teets , Jon William Teets
发明人： Joseph Michael Teets , Jon William Teets
IPC分类号： F02G3/00
CPC分类号： F02C6/18 , F01D15/10 , F05B2220/62 , F05D2250/82 , Y02E20/14
摘要： A power plant with a CHP system having a distillation apparatus to yield a high thermally efficient electrical power plant for reduced fuel usage and subsequent lower CO2 emission specie. The incorporation of a Combined Heat and Power (CHP) system with a microturbine, makes use of the low emissions gas turbine exhaust gas waste heat of this electrical power generation plant for distillation processes, replacing the current use of electrical heating elements of the distiller unit. The inventive device includes a distiller apparatus and a microturbine gas turbine electrical power plant, a heat exchanger device where the exhaust gas waste heat energy of a gas turbine power plant passes thru one side of a series of plates/sheets of material and or tubes and heats the process fluids on the opposite side and also a surface area condenser is incorporated to reduce the product vapor state to a liquid.
摘要翻译：具有CHP系统的发电厂具有蒸馏装置，以产生用于减少燃料使用的高热效率电力设备和随后的较低二氧化碳排放物质。将热电联产系统（CHP）与微型涡轮机相结合，利用该发电厂的低排放燃气轮机废气废热进行蒸馏处理，取代目前使用蒸馏装置的电加热元件。本发明的装置包括一个蒸馏器装置和一个微型涡轮燃气轮机发电厂，一个热交换器装置，其中燃气轮机发电厂废气废热通过一系列板/材料和/或管的一侧，加热相对侧上的工艺流体，并且还加入表面积冷凝器以将产物蒸气状态降低至液体。

4. 发明申请

US20080041059A1 Radially staged RQL combustor with tangential fuel premixers 有权
标题翻译：带切向燃料预混合器的径向分级RQL燃烧器
公开(公告)号：US20080041059A1
公开(公告)日：2008-02-21
申请号：US11820427
申请日：2007-06-19
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F23R3/32
CPC分类号： F23R3/52 , F23C2900/06041 , F23D14/66 , F23R3/286 , F23R3/32 , F23R3/36 , Y02E20/348
摘要： A double annular radially staged combustor having an axially reduced common internal flow transitioning area between outboard primary combustion zone and inboard secondary combustion zone. The primary zone geometry is generally a toroidal shell form with a radially inboard wall annular exiting thru flow area into the secondary fuel air premixing section. Fuel and Air premixing chambers are incorporated into the primary combustion zone with vaporization capability for liquid fuels. The secondary zone is of an annular shell form, generally inboard and adjacent to the primary zone, accepts the primary combustion gases and mixes with additional supplied air in a reduced annular flow area and then combusted in the secondary combustion zone. The secondary combustion zone exiting gas, flows into a dilution zone where further air is mixed and with continued flow downstream this heat energy is delivered to the turbine stage of a gas turbine engine.
摘要翻译：双环形径向分级燃烧器，其在外侧主燃烧区和内侧二次燃烧区之间具有轴向减小的公共内部流动过渡区域。主区域几何形状通常是环形壳体形式，其具有径向内侧壁环形，通过流动区域流入二次燃料空气预混合段。燃料和空气预混合室被并入主燃烧区，具有用于液体燃料的汽化能力。次级区域是环形壳体形式，通常在主区域内并且邻近初级区域，接受初级燃烧气体并与减少的环形流动区域中的附加供应空气混合，然后在二级燃烧区域中燃烧。离开气体的二次燃烧区域流入稀释区域，其中进一步的空气被混合，并且在下游继续流动，该热能被输送到燃气涡轮发动机的涡轮机级。

5. 发明授权

US10422534B2 Fuel air premix chamber for a gas turbine engine 有权
公开(公告)号：US10422534B2
公开(公告)日：2019-09-24
申请号：US13986905
申请日：2013-06-17
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F23R3/28 , F23D11/38 , F23D14/64 , F23R3/34 , F23R3/58
摘要： An improved fuel air premix chamber for a gas turbine engine. An integral heat exchange structure is used to cools the premix chamber outer wall, preheating the compressor air supply as it passes into an inner central longitudinal premix tube and preheating also the fuel and F/A mixture for an improved mix, low emissions combustion and low differential combustor pressure. The F/A premix flow thru the central longitudinal tubes and yields an exiting spouting velocity into the primary combustion zone for swirl/circumferential flow combustion yielding flame stability.

6. 发明申请

US20160172931A1 Alternator rotor to stator integrated hrdrodynamic bearing 审中-公开
标题翻译：发电机转子定子集成小动力轴承
公开(公告)号：US20160172931A1
公开(公告)日：2016-06-16
申请号：US14544233
申请日：2014-12-11
申请人： Joseph Michael Teets , Jon William Teets
发明人： Joseph Michael Teets , Jon William Teets
IPC分类号： H02K7/08
CPC分类号： H02K21/24 , H02K5/1677 , H02K7/088
摘要： A hydrodynamic bearing is incorporated within an alternator electrical generating system and or electric motors having permanent magnet (PM) machine rotors wherein a fluid film bearing is integrated between the rotor assembly outer diameter and the electrical stator assembly inner diameter. The alternator rotor outside diameter is a bearing surface and a static sleeve bearing is positioned inboard of the electrical stator inner diameter, coaxially and central, wherein the static sleeve inner diameter is a bearing surface. An additional select material is incorporated to sleeve bearing inner diameter surface to prevent relative surface damage during none fluid film operating conditions.A gas pressurized system, incorporated as the fluid means yields improved bearing life, reduced machine axial rotor system length and reduced costs in high speed alternators and or motors applications such as in turbomachinery, alternators for generating electricity, Microturbines, hybrid gas turbine engines removing the need for external bearings.
摘要翻译：流体动力轴承结合在交流发电机发电系统中，或者具有永磁体（PM）机器转子的电动机，其中流体膜轴承集成在转子组件外径和电子定子组件内径之间。交流发电机转子外径是轴承表面，并且静止套筒轴承位于电子定子内径的同轴和中心的内侧，其中静态套筒内径是支承表面。另外的选择材料被结合到套筒轴承内径表面以防止在没有流体膜操作条件期间的相对表面损坏。作为流体装置并入的气体加压系统产生改善的轴承寿命，降低机器轴向转子系统长度并降低高速交流发电机和/或电动机应用中的成本，例如在涡轮机械，用于发电的交流发电机，微型涡轮机，混合燃气涡轮发动机需要外部轴承。

7. 发明申请

US20140366542A1 Fuel Air Premix Chamber For a Gas Turbine Engine 审中-公开
标题翻译：用于燃气轮机的燃料空气预混室
公开(公告)号：US20140366542A1
公开(公告)日：2014-12-18
申请号：US13986905
申请日：2013-06-17
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F23R3/28
摘要： Fuel/air premixing chambers are applied to a gas turbine combustor RQL or LPP type integrated to the combustor with extension into the combustion zone. An integral heat exchange structure cools the premix chamber outer wall, preheating the compressor air supply as it passes into an inner central longitudinal premix tube preheating also the fuel and F/A mixture for improved mixedness, low emissions combustion and low differential combustor pressure.The F/A premix flow thru the central longitudinal tubes yields an exiting spouting velocity into the primary combustion zone for swirl/circumferential flow combustion yielding flame stability. Circumferentially close spaced premixing chambers about the combustor outer wall, are tangentially positioned for internal combustion hot gas flow, preheating the adjacent premix chamber and generates internal sweeping hot gas flow preventing combustion chamber carbon issues. Incorporates low pressure fuel injection into a central longitudinal tube for reduced cost and system simplicity.
摘要翻译：燃料/空气预混合室被施加到与燃烧器一体化的燃气轮机燃烧器RQL或LPP，其延伸到燃烧区域中。整体热交换结构冷却预混室外壁，当压缩机空气供应进入内部中央纵向预混管时，也预热燃料和F / A混合物以改善混合度，低排放燃烧和低差压燃烧器压力。通过中央纵向管的F / A预混合流产生进入主燃烧区的离开喷射速度，用于涡流/周向流动燃烧产生火焰稳定性。围绕燃烧器外壁的周向间隔开的预混合室被切向定位用于内部燃烧热气流，预热相邻的预混合室并产生防止燃烧室碳问题的内部扫掠热气流。将低压燃料喷射引入中央纵管，以降低成本和系统简单性。

8. 发明授权

US07211906B2 Rankine—microturbine for generating electricity 失效
标题翻译：兰金微发电机发电
公开(公告)号：US07211906B2
公开(公告)日：2007-05-01
申请号：US11393204
申请日：2006-03-30
申请人： Joseph Michael Teets , Jon William Teets
发明人： Joseph Michael Teets , Jon William Teets
IPC分类号： F02C60/20
CPC分类号： F01D15/10 , F02C6/18 , F05D2220/72 , F05D2220/76 , F05D2250/82 , F05D2260/85 , Y02E20/14
摘要： An electrical output power generation system is provided. A gas turbine engine rotor spool with at least one alternator rotor and steam turbine rotor are integrated and within a engine body having a combustor or external heat source having fluid communication with the bladed compressor rotor and a gas turbine bladed rotor of the said rotor spool. The alternator rotor has permanent magnets retained and positioned in close proximity and co-axial to the electrical stator having iron laminat and electrical wires. Relative rotational motion between the electrical stator and alternator rotor cause magnetic flux and subsequent electricity to be generated. The steam energy to drive the said rotor spool integrated steam turbine rotor can be from the gas turbine engine exhaust waste heat and or thru external heat energy sources.
摘要翻译：提供电力输出发电系统。具有至少一个交流发电机转子和蒸汽涡轮机转子的燃气涡轮发动机转子阀芯被集成在发动机主体内，该发动机主体具有与叶片压缩机转子和所述转子阀芯的燃气轮机叶片转子流体连通的燃烧器或外部热源。交流发电机转子具有保持并定位成紧密并且与具有铁层压板和电线的电定子同轴的永磁体。电子定子和交流发电机转子之间的相对旋转运动引起磁通量和随后的电力产生。用于驱动所述转子卷轴的蒸汽能量集成汽轮机转子可以来自燃气涡轮发动机废气余热或通过外部热能源。

9. 发明公开

US20230392547A1 Advanced 2-spool turboprop engine 审中-公开
公开(公告)号：US20230392547A1
公开(公告)日：2023-12-07
申请号：US18452214
申请日：2023-08-18
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F02C3/10 , F02C7/32 , F02C7/36
CPC分类号： F02C3/103 , F02C7/32 , F02C7/36 , F05D2220/323
摘要： A low cost, high power density, low emissions general aviation turbine engine (GATE) with improved fuel economy over current engines. Ideally suited for 50 to 500 shaft horsepower (SHP) range aircraft applications such as GA, UAS, UAS, air taxi, helicopters and commercial markets. The engine design features with centrifugal compressor and radial turbine rotors has a high-end practical limit of ˜800 (SHP). The new turboprop incorporates 2 non-concentric spools aero-thermal-pressure coupled wherein staged compressor rotors lend to a simple engine design, optimized high overall engine pressure ratio (OPR) and low specific fuel consumption (SFC). An integral starter—generator system further simplifies the engine design and offers high electrical output power capability for auxiliary power requirements. A 2-stage low emissions combustor with fuel-air premix chambers is incorporated lending to stable combustion at any engine spool speed/power requirement, further fuel optimization and use of a low cost simple fixed pitch propeller. Some other highlights include: any fuel or mixture thereof, TBO greater than piston or other turbine engines, less maintenance costs, oil/filter change at ˜15000 hrs. and other inherent advantages of a gas turbine engine.
Of the two spools that make up this turboprop engine, one is the High Pressure (HP) spool that is part of the gas generator using combustor hot gases to power the integral HP turbine rotor, HP compressor and high-speed alternator starter—generator. The other engine spool is the Low-Pressure (LP) spool that receives the HP turbine exhaust heat energy to power the integral LP compressor rotor, LP turbine rotor, integrated gearbox with resultant output shaft horsepower.
This invention represents the most advanced engine for general aviation since Charles Edward Taylor's engine powered the Wright Brothers first aircraft-controlled powered flight Dec. 17, 1903.

10. 发明授权

US11788464B2 Advanced 2-spool turboprop engine 有权
公开(公告)号：US11788464B2
公开(公告)日：2023-10-17
申请号：US16873610
申请日：2020-05-22
申请人： Joseph Michael Teets
发明人： Joseph Michael Teets
IPC分类号： F02C3/10 , F02C7/32 , F02C7/36
CPC分类号： F02C3/103 , F02C7/32 , F02C7/36 , F05D2220/323
摘要： A low cost, high power density, low emissions general aviation turbine engine (GATE) with improved fuel economy over current engines. Ideally suited for 50 to 500 shaft horsepower (SHP) range aircraft applications such as GA, UAS, UAS, air taxi, helicopters and commercial markets. The engine design features with centrifugal compressor and radial turbine rotors has a high-end practical limit of ˜800 (SHP). The new turboprop incorporates 2 non-concentric spools aero-thermal—pressure coupled wherein staged compressor rotors lend to a simple engine design, optimized high overall engine pressure ratio (OPR) and low specific fuel consumption (SFC). An integral starter-generator system further simplifies the engine design and offers high electrical output power capability for auxiliary power requirements. A 2-stage low emissions combustor with fuel-air premix chambers is incorporated lending to stable combustion at any engine spool speed/power requirement, further fuel optimization and use of a low cost simple fixed pitch propeller. Some other highlights include: any fuel or mixture thereof, TBO greater than piston or other turbine engines, less maintenance costs, oil/filter change at ˜15000 hrs. and other inherent advantages of a gas turbine engine.
Of the two spools that make up this turboprop engine, one is the High Pressure (HP) spool that is part of the gas generator using combustor hot gases to power the integral HP turbine rotor, HP compressor and high-speed alternator starter—generator. The other engine spool is the Low-Pressure (LP) spool that receives the HP turbine exhaust heat energy to power the integral LP compressor rotor, LP turbine rotor, integrated gearbox with resultant output shaft horsepower.
This invention represents the most advanced engine for general aviation since Charles Edward Taylor's engine powered the Wright Brothers first aircraft-controlled powered flight Dec. 17, 1903.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式