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公开(公告)号：US07562519B1
公开(公告)日：2009-07-21
申请号：US11219617
申请日：2005-09-03
Applicant: Mark M. Harris , Wesley D. Brown , Angel M. Garcia
Inventor： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
CPC classification number: F01D25/162 , F01D25/125 , F02C7/06 , F16C19/163 , F16C33/58 , F16C37/007 , Y10S384/90
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US09394799B1
公开(公告)日：2016-07-19
申请号：US14795095
申请日：2015-07-09
Applicant: Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
Inventor： Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
CPC classification number: F01D11/025 , F01D11/003 , F16J15/34 , F16J15/3448
Abstract: An air riding seal between a rotor and a stator in a turbine of a gas turbine engine, where an annular piston is movable in an axial direction within a housing that extends from the stator, and a bellows is secured to the annular piston to form a flexible air passageway from a compressed air inlet through the annular piston and into a cushion cavity that forms an air riding seal between the annular piston and the rotor sealing surface. In another embodiment, a flexible seal secured to and extending from the annular piston forms a sealing surface between the annular piston chamber and the annular piston to provide a seal and allow for axial movement.
Abstract translation: 在燃气涡轮发动机的涡轮机中的转子和定子之间的空气骑行密封件，其中环形活塞在从定子延伸的壳体内的轴向方向上可移动，并且波纹管固定到环形活塞以形成 柔性空气通道从压缩空气入口通过环形活塞并进入缓冲腔，其在环形活塞和转子密封表面之间形成空气密封。 在另一个实施例中，固定到环形活塞并从环形活塞延伸的柔性密封件在环形活塞室和环形活塞之间形成密封表面，以提供密封并允许轴向移动。
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公开(公告)号：US20120234016A1
公开(公告)日：2012-09-20
申请号：US13481089
申请日：2012-05-25
Applicant: Mark M. Harris , Wesley D. Brown , Angel M. Garcia
Inventor： Mark M. Harris , Wesley D. Brown , Angel M. Garcia
CPC classification number: F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
Abstract: 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.
Abstract translation: 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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公开(公告)号：US08052391B1
公开(公告)日：2011-11-08
申请号：US12410489
申请日：2009-03-25
Applicant: Wesley D Brown
Inventor： Wesley D Brown
IPC: F01D5/18
CPC classification number: F01D5/188 , F01D5/147 , Y10T29/49341 , Y10T29/49343
Abstract: A turbine rotor blade made from the spar and shell construction in which the shell is a thin wall shell made from a high temperature resistant material that is formed by a wire EDM process, and where the shell is secured to the spar using a retainer that is poured into retainer occupying spaces formed in the shell and the spar, and then hardened to form a rigid retainer to secure the shell to the spar. The spar and the shell both have grooves facing each other to form a retainer groove. A retaining material, such as a liquid or a powdered metal, is poured into the grooves and hardened to form a retainer to secure the shell to the spar. The retaining material also forms a seal on the top of the spar and between the spar and shell.
Abstract translation: 一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体是由通过线材EDM工艺形成的耐高温材料制成的薄壁壳，并且其中壳体使用保持器固定到翼梁 倒入形成在壳体和翼梁中的保持器占据空间中，然后硬化以形成刚性保持器以将壳固定到翼梁。 翼梁和壳体都具有彼此面对的槽以形成保持器槽。 将诸如液体或粉末金属的保持材料倒入槽中并硬化以形成保持器以将壳固定到翼梁。 保持材料也在翼梁的顶部和翼梁和壳体之间形成密封。
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公开(公告)号：US07670116B1
公开(公告)日：2010-03-02
申请号：US11243308
申请日：2005-10-04
Applicant: Jack W. Wilson, Jr. , Wesley D Brown
Inventor： Jack W. Wilson, Jr. , Wesley D Brown
IPC: F01D5/14
CPC classification number: F01D5/147 , F01D5/189 , F01D5/20 , Y10T29/49327 , Y10T29/49339 , Y10T29/49341
Abstract: The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from either Molybdenum, Niobium, alloys of Molybdenum or Niobium (Columbium), Oxide Ceramic Matrix Composite (CMC), or SiC—SiC ceramic matrix composite, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane.
Abstract translation: 本发明是一种用于燃气涡轮发动机的叶片，其中叶片由难以加工或铸造的外来高温材料制成。 叶片包括由钼，铌，钼或铌（铌），氧化物陶瓷基复合材料（CMC）或SiC-SiC陶瓷基体复合材料制成的壳体，并由导线放电工艺形成。 壳体定位在外护罩之间的凹槽中，并且在翼梁内部包括中心通道，并且在翼梁和壳体之间形成冷却流体通道。 翼梁和壳都包括冷却孔，以将冷却流体从中心通道运送到叶片的外表面用于冷却。 该冷却路径消除了蛇形通道，因此需要较少的压力和较少量的冷却流体来冷却叶片。
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Patent Agency Ranking
公开(公告)号：US06413044B1
公开(公告)日：2002-07-02
申请号：US09609052
申请日：2000-06-30
Applicant: Norman Roeloffs , Wesley D. Brown
Inventor： Norman Roeloffs , Wesley D. Brown
IPC: F04D2970
CPC classification number: F01D5/187 , F01D25/32 , F05D2250/314 , F05D2250/322 , F05D2250/52 , F05D2260/205 , F05D2260/607
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US5403156A
公开(公告)日：1995-04-04
申请号：US143681
申请日：1993-10-26
Applicant: Brian P. Arness , Wesley D. Brown
Inventor： Brian P. Arness , Wesley D. Brown
CPC classification number: F01D5/081 , F01D5/3007 , Y10T29/49321 , Y10T29/49341
Abstract: 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.
Abstract translation: 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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公开(公告)号：US4820122A
公开(公告)日：1989-04-11
申请号：US185227
申请日：1988-04-25
Applicant: Kenneth B. Hall , Thomas A. Auxier , Wesley D. Brown
Inventor： Kenneth B. Hall , Thomas A. Auxier , Wesley D. Brown
CPC classification number: F01D25/32 , F01D5/187 , F05D2260/607 , Y02T50/676
Abstract: Dirt removal means for an internally air cooled blade for a gas turbine engine of the type that includes multi passes some of which are serpentine as made in situ by casting the ribs so as to be angularly disposed at the root of the blade and a straight through passageway with an opening at the tip. The velocity of the airstream in the straight through passageway being sufficiently high to carry the dirt through the opening and the angularly disposed ribs overlying the entrance to the other passageway so as to divert the dirt entrained airstream into the straight through passageway while allowing relatively dirt-free air to turn the angle of the rib to enter the serpentine passes.
Abstract translation: 用于燃气涡轮发动机的内部空气冷却叶片的除尘装置，其包括多次通过，其中一些是通过浇铸肋原位制造的蛇形，以便成角度地设置在叶片的根部处，并且直线穿过 在尖端具有开口的通道。 直通通道中的气流的速度足够高以将污物通过开口和角度布置的肋覆盖在另一通道的入口上，以将污物夹带的气流转移到直通通道中，同时允许相对污垢 - 自由空气转动肋骨的角度进入蛇纹通道。
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公开(公告)号：US10024170B1
公开(公告)日：2018-07-17
申请号：US15203905
申请日：2016-07-07
Applicant: Robert L Memmen , Wesley D Brown
Inventor： Robert L Memmen , Wesley D Brown
Abstract: An integrally bladed rotor with an axial bore having either an inward dishing shape or an axial straight shape with an annular inward projection in which radial cooling holes having an elliptical cross sectional shape are formed, where the radial cooling holes have an elliptical cross sectional shape with a major axis perpendicular to the axial bore in order to reduce stress near an inlet opening of the radial holes in order to increase the LCF life of the IBR. The radial cooling holes discharge into a circumferential channel that is connected to cooling holes extending in the rotor blades.
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公开(公告)号：US08307661B2
公开(公告)日：2012-11-13
申请号：US13481089
申请日：2012-05-25
Applicant: Mark M. Harris , Wesley D. Brown , Angel M. Garcie
Inventor： Mark M. Harris , Wesley D. Brown , Angel M. Garcie
IPC: F02C1/00
CPC classification number: F02C7/22 , F01D25/12 , F02C3/14 , F05D2250/80 , F23R3/38
Abstract: 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.
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