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1. 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.

2. 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。

3. 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.

4. 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。

5. 发明授权

US07562519B1 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：US07562519B1
公开(公告)日：2009-07-21
申请号：US11219617
申请日：2005-09-03
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： F02C7/06 , 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 with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support 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 sued 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：具有位于燃烧器下游的压缩机，燃烧器和涡轮的小型燃气涡轮发动机。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。涡旋杯喷射器被起动以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。

6. 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。

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

US5243759A Method of casting to control the cooling air flow rate of the airfoil trailing edge 失效
标题翻译：用于控制翼型后缘的冷却空气流量的铸造方法
公开(公告)号：US5243759A
公开(公告)日：1993-09-14
申请号：US772296
申请日：1991-10-07
申请人： Wesley D. Brown , Kenneth B. Hall , Robert J. Kildea
发明人： Wesley D. Brown , Kenneth B. Hall , Robert J. Kildea
IPC分类号： B22C9/10 , B23P13/00 , B23P15/02 , F01D5/18
CPC分类号： B22C9/10 , B23P13/00 , B23P15/02 , F01D5/187 , F05D2260/202 , F05D2260/2212 , Y02T50/676 , Y10T29/49336 , Y10T29/49341 , Y10T29/49776
摘要： The flow rate of the cooling air at the trailing edge of the airfoil of a turbine blade for a gas turbine engine is established by casting the blade to include judiciously located radially spaced projections adjacent to or in the ribs in the trailing edge which serve to meter the flow in the channels formed between the ribs. The holes for forming the projections in the core that are used to form the internal cooling passages in the trailing edge are intentionally undersized. After the core is cleaned and flashed, the blade is cast in a mold and the ceramic core is leached out. The internal cooling passages in the trailing edge are flow tested to obtain the flow rate and pressure and this data is used to resize the projection. Resizing the projection is made by reforming the core with the same die, and with the information previously obtained in the flow test, the holes that form the projections are enlarged by drilling to obtain the desired flow rate. This process is repeated until the desired flow rate for each trailing edge channel is achieved. The die may be changed at this juncture to provide the ultimate dimensioned hole in the core to provide the necessary metering of the cooling air to attain the predetermined flow rate.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片的翼缘的后缘处的冷却空气的流速通过铸造刀片来建立，该刀片包括与用于计量的后缘相邻或位于后缘的肋中的明显位于的径向间隔的突出部在肋之间形成的通道中的流动。用于在芯中形成用于在后缘形成内部冷却通道的突起的孔有意地小型化。在芯体被清洗和闪光之后，将刀片浇铸在模具中，并将陶瓷芯浸出。后缘中的内部冷却通道被流动测试以获得流量和压力，并且该数据用于调整投影尺寸。通过使用相同的模具对芯体进行重新调整大小，并且利用流动测试中先前获得的信息，通过钻孔来扩大形成突起的孔以获得期望的流量。重复该过程，直到实现每个后缘通道的期望流量。此时可以改变模具，以在芯体中提供极限尺寸的孔，以提供冷却空气的必要计量以达到预定流量。

9. 发明授权

US06413044B1 Blade cooling in gas turbine 失效
标题翻译：燃气轮机叶片冷却
公开(公告)号：US06413044B1
公开(公告)日：2002-07-02
申请号：US09609052
申请日：2000-06-30
申请人： Norman Roeloffs , Wesley D. Brown
发明人： Norman Roeloffs , Wesley D. Brown
IPC分类号： F04D2970
CPC分类号： F01D5/187 , F01D25/32 , F05D2250/314 , F05D2250/322 , F05D2250/52 , F05D2260/205 , F05D2260/607
摘要： A gas turbine whose blades are cooled with cooling air has in its turbine part a device for the removal of dirt particles from the cooling air. The device consists of a first chamber in which the cooling air is collected, and a second chamber into which the cooling air from the first chamber is fed through conduit, and in which the dirt particles are removed from the cooling air. The conduit, above which a drop in pressure occurs, are oriented at an angle (&phgr;) in relation to the rotor axis so that the cooling air is accelerated in the tangential direction in relation to the rotor and moves in the circumferential direction of the rotor within the second chamber. Dirt particles are removed in the second chamber by centrifugal force from the cooling air in that they are driven outward and pass through the outlet openings into the gas stream of the turbine. The clean cooling air exits through radially further inward outlet openings into the cooling channels of the blades.
摘要翻译：其叶片用冷却空气冷却的燃气轮机在其涡轮机部分具有用于从冷却空气中除去污垢颗粒的装置。该装置包括收集冷却空气的第一室和第二室，来自第一室的冷却空气通过第二室被供给到导管中，并且其中灰尘颗粒从冷却空气中除去。导致压力下降的导管相对于转子轴线以角度（phi）取向，使得冷却空气相对于转子沿切线方向加速并沿转子的圆周方向移动在第二个房间内。通过来自冷却空气的离心力在第二室中除去污垢颗粒，因为它们被向外驱动，并通过出口开口进入涡轮机的气流。清洁的冷却空气通过径向进一步向内的出口进入叶片的冷却通道。

10. 发明授权

US5403156A Integral meter plate for turbine blade and method 失效
标题翻译：涡轮叶片积分仪表及方法
公开(公告)号：US5403156A
公开(公告)日：1995-04-04
申请号：US143681
申请日：1993-10-26
申请人： Brian P. Arness , Wesley D. Brown
发明人： Brian P. Arness , Wesley D. Brown
IPC分类号： F01D5/18 , F01D5/08 , F01D5/30 , F02C7/18
CPC分类号： F01D5/081 , F01D5/3007 , Y10T29/49321 , Y10T29/49341
摘要： A meter plate formed from a depending member extending from the root of a turbine blade just short of the edge of the bottom of the broach in the disk in the live rim area is cast integrally with the blade and serves to meter coolant flow from the on board injector to internally of the blade. The final dimension can be configured in the machining operation of the blade to attain the desired amount of coolant flow for internal blade cooling.
摘要翻译：从靠近涡轮叶片的根部延伸的仪表板，其刚好短于活动边缘区域中的盘中的拉刀的底部边缘，与叶片一体地铸造，用于测量来自板式进样器到刀片内部。可以在刀片的加工操作中配置最终尺寸，以获得用于内部叶片冷却的所需量的冷却剂流。

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