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1. 发明授权

US5237813A Annular combustor with outer transition liner cooling 失效
标题翻译：具有外过渡衬垫冷却的环形燃烧器
公开(公告)号：US5237813A
公开(公告)日：1993-08-24
申请号：US934053
申请日：1992-08-21
申请人： Mark M. Harris , David N. Marsh
发明人： Mark M. Harris , David N. Marsh
IPC分类号： F23R3/02 , F23R3/50 , F23R3/54
CPC分类号： F23R3/54 , F23R3/02 , F23R3/50
摘要： A reverse flow annular combustor is provided having downstream wall comprised of a shroud covering the outer surface of the outer transition liner. The shroud abuts the transition liner at a plurality of points to define a plurality of passages between the shroud and the liner. The passages receiving cooling through the shroud at its radial inner end and expel the cooling air through the liner at its outer radial portion and into the hot gas in the combustor. Thus, the air used to cool the liner is also used for dilution mixing with the combustion gas.
摘要翻译：设置有逆流环形燃烧器，其具有由覆盖外过渡衬套的外表面的护罩组成的下游壁。护罩在多个点处邻接过渡衬垫以限定护罩和衬套之间的多个通道。通道在其径向内端处通过护罩冷却，并且通过衬套在其外部径向部分排出冷却空气并将其排入燃烧器中的热气体。因此，用于冷却衬套的空气也用于与燃烧气体的稀释混合。

2. 发明授权

US08196407B2 Small gas turbine engine with multiple burn zones 有权
公开(公告)号：US08196407B2
公开(公告)日：2012-06-12
申请号：US12487882
申请日：2009-06-19
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
IPC分类号： F02C3/00
CPC分类号： F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.

3. 发明授权

US6148601A Engine fuel control system and method 失效
标题翻译：发动机燃油控制系统及方法
公开(公告)号：US6148601A
公开(公告)日：2000-11-21
申请号：US75130
申请日：1998-05-08
申请人： Anthony Charles Jones , Mark M. Harris , David R. Ripley , Malcolm J. McArthur
发明人： Anthony Charles Jones , Mark M. Harris , David R. Ripley , Malcolm J. McArthur
IPC分类号： F02C9/26 , F02C9/28
CPC分类号： F02C9/263 , F02C9/28
摘要： Accuracy and predictability are provided in a fuel control system for an engine system including a fuel supply and a combustion chamber. The fuel control system includes at least one fuel injector having a calibrated nozzle to direct a fuel flow from the fuel supply into the combustion chamber of the engine, a servo valve connected between the fuel supply and the calibrated nozzle to meter the fuel flow from the fuel supply to the calibrated nozzle, a pressure transducer operably associated with the calibrated nozzle to measure a pressure drop in the fuel flow across the calibrated nozzle, and a controller operably associated with the pressure transducer and the servo valve to control the metering of the fuel flow by the servo valve. The calibrated nozzle has a known fuel flow vs. pressure drop characteristic. The controller controls the metering of the fuel flow by the servo valve based on the pressure drop measured by the pressure transducer and the known fuel flow vs. pressure drop characteristic of the calibrated nozzle.
摘要翻译：在包括燃料供应和燃烧室的发动机系统的燃料控制系统中提供了精度和可预测性。燃料控制系统包括至少一个具有校准喷嘴的燃料喷射器，用于将来自燃料供应的燃料流引导到发动机的燃烧室中，连接在燃料供应和校准喷嘴之间的伺服阀，燃料供应到校准喷嘴，与校准喷嘴可操作地相关联的压力传感器，以测量穿过校准喷嘴的燃料流中的压降;以及与压力传感器和伺服阀可操作地相关联以控制燃料计量的控制器由伺服阀流动。校准喷嘴具有已知的燃料流量对压降特性。控制器基于由压力传感器测量的压降和已知的燃料流量对校准喷嘴的压降特性来控制由伺服阀计量燃料流量的计量。

4. 发明申请

US20120234016A1 Small gas turbine engine with multiple burn zones 有权
标题翻译：具有多个燃烧区的小型燃气轮机
公开(公告)号：US20120234016A1
公开(公告)日：2012-09-20
申请号：US13481089
申请日：2012-05-25
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
IPC分类号： F23R3/34 , F02C7/228
CPC分类号： F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.
摘要翻译：一种用于诸如巡航导弹的无人机的小型燃气涡轮发动机，燃气轮机具有形成初级燃烧区和次级燃烧区的燃烧器，其中通过以下任一方式将燃料喷射到主燃烧区域和次燃烧区域中旋转杯喷射器或多个燃料喷射器喷嘴。具有单独燃料喷射的二次燃烧区允许发动机的直径减小，但是仍然允许达到足够的动力和效率来为车辆供电。来自压缩机的空气流被用于在被注入到燃烧器中之前冷却燃烧器壁，并且在引入燃烧器之前，使引导喷嘴和位于燃烧器的热部附近的主轴承通过并冷却。

5. 发明授权

US06931862B2 Combustor system for an expendable gas turbine engine 有权
标题翻译：用于消耗式燃气涡轮发动机的燃烧器系统
公开(公告)号：US06931862B2
公开(公告)日：2005-08-23
申请号：US10426314
申请日：2003-04-30
申请人： Mark M. Harris
发明人： Mark M. Harris
IPC分类号： F23R3/04 , F23R3/12 , F23R3/28 , F23R3/50 , F23R3/58
CPC分类号： F23R3/50 , F23R3/045 , F23R3/12 , F23R3/286 , Y02T50/675
摘要： A combustor system for a miniature gas turbine engine includes fuel injection via orifices which direct fuel into fuel-air injection tubes which feed a fuel-rich mixture of fuel and air into a leading end of the combustor liner to form a primary burning region. Fuel system pressures are kept low and controlled by control of the fuel injection port size and number. Fuel breakup is via airblast and tube wall impingement. The fuel-air injection tubes are directed circumferentially, radially outward and toward the front end of the combustor. Air is fed into the combustor such that two distinct burning regions are created. Each region approximates a “well-stirred reactor” and the combination of the two regions results in an efficient use of combustion volume.
摘要翻译：用于微型燃气涡轮发动机的燃烧器系统包括经由喷嘴的燃料喷射，所述喷嘴将燃料引导到燃料空气喷射管中，所述燃料 - 空气喷射管将燃料和空气的富燃料混合物供给到燃烧器衬套的前端以形成初级燃烧区域。燃料系统压力保持较低，并且通过控制燃料喷射口的尺寸和数量来控制。燃油分解是通过喷气和管壁冲击。燃料空气注入管沿周向，径向向外并朝向燃烧器的前端定向。空气进入燃烧器，从而形成两个不同的燃烧区域。每个区域近似于“良好搅拌的反应器”，并且两个区域的组合导致有效地使用燃烧体积。

6. 发明授权

US08307661B2 Small gas turbine engine with multiple burn zones 有权
公开(公告)号：US08307661B2
公开(公告)日：2012-11-13
申请号：US13481089
申请日：2012-05-25
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
IPC分类号： F02C1/00
CPC分类号： F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.

7. 发明申请

US20100229560A1 Small gas turbine engine with multiple burn zones 有权
标题翻译：具有多个燃烧区的小型燃气轮机
公开(公告)号：US20100229560A1
公开(公告)日：2010-09-16
申请号：US12487882
申请日：2009-06-19
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.
摘要翻译：一种用于诸如巡航导弹的无人机的小型燃气涡轮发动机，燃气轮机具有形成初级燃烧区和次级燃烧区的燃烧器，其中通过以下任一方式将燃料喷射到主燃烧区域和次燃烧区域中旋转杯喷射器或多个燃料喷射器喷嘴。具有单独燃料喷射的二次燃烧区允许发动机的直径减小，但是仍然允许达到足够的动力和效率来为车辆供电。来自压缩机的空气流被用于在被注入到燃烧器中之前冷却燃烧器壁，并且在引入燃烧器之前，使引导喷嘴和位于燃烧器的热部附近的主轴承通过并冷却。

8. 发明授权

US07685822B1 Rotary cup fuel injector 有权
标题翻译：旋转杯燃油喷射器
公开(公告)号：US07685822B1
公开(公告)日：2010-03-30
申请号：US11271731
申请日：2005-11-09
申请人： Mark M. Harris
发明人： Mark M. Harris
IPC分类号： F02C7/22
CPC分类号： F02C7/22
摘要： A rotary cup fuel injector for use in a gas turbine engine, the rotary cup injector being rotatably secured to the rotor shaft and positioned radially inward of the combustor, the rotary cup injector having a front face with a parabolic shape and a rear face with a slanted and flat shape. The front and rear faces of the injector form a thin film of fuel on the surfaces and—because of the high rotational speed—produce fine droplet's of fuel to be injected into a combustion chamber. The two faces inject fuel into two combustion zones of the combustor.
摘要翻译：一种用于燃气涡轮发动机的转杯式燃料喷射器，旋转杯式喷射器可旋转地固定在转子轴上并且位于燃烧器的径向内侧，旋转杯式喷射器具有抛物面形状的前表面和具有抛物面形状的后表面倾斜平坦的形状。喷射器的前表面和后表面在表面上形成一薄层燃料，由于高旋转速度 - 产生要喷射到燃烧室中的精细液滴的燃料。两个面将燃料喷入燃烧器的两个燃烧区域。

9. 发明授权

US07997057B1 Gas turbine engine with an air cooled bearing 有权
标题翻译：具有空气冷却轴承的燃气涡轮发动机
公开(公告)号：US07997057B1
公开(公告)日：2011-08-16
申请号：US12487903
申请日：2009-06-19
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
IPC分类号： F02C7/06 , F16C19/50
CPC分类号： F01D25/162 , F01D25/125 , F02C7/06 , F16C19/163 , F16C33/58 , F16C37/007 , Y10S384/90
摘要： A small gas turbine engine where the compressor and turbine are supported on a rotary shaft, and a main bearing is supported on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is used to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.
摘要翻译：一种小型燃气轮机，其中压缩机和涡轮机支撑在旋转轴上，主轴承支撑在旋转轴上，主轴承位于燃烧器的热区中。主轴承包括座圈内的冷却空气通道，为轴承提供冷却。冷却空气从压缩机转向并通过轴承冷却通道以冷却轴承，然后冷却空气被引导到燃烧器中。冷却空气在通过轴承之前也通过引导喷嘴，以冷却引导喷嘴和轴承。涡旋杯喷射器用于将来自压缩机的压缩空气和来自轴承的冷却空气输送到燃烧器中，旋转杯喷射器还用于将冷却空气抽吸通过轴承。

10. 发明授权

US07568343B2 Small gas turbine engine with multiple burn zones 有权
标题翻译：具有多个燃烧区的小型燃气轮机
公开(公告)号：US07568343B2
公开(公告)日：2009-08-04
申请号：US11224906
申请日：2005-09-12
申请人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
发明人： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
IPC分类号： F02C3/00
CPC分类号： F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
摘要： A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.
摘要翻译：一种用于诸如巡航导弹的无人机的小型燃气涡轮发动机，燃气轮机具有形成初级燃烧区和次级燃烧区的燃烧器，其中通过以下任一方式将燃料喷射到主燃烧区域和次燃烧区域中旋转杯喷射器或多个燃料喷射器喷嘴。具有单独燃料喷射的二次燃烧区允许发动机的直径减小，但是仍然允许达到足够的动力和效率来为车辆供电。来自压缩机的空气流被用于在被注入到燃烧器中之前冷却燃烧器壁，并且在引入燃烧器之前，使引导喷嘴和位于燃烧器的热部附近的主轴承通过并冷却。

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