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

US07942009B1 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：US07942009B1
公开(公告)日：2011-05-17
申请号：US12484503
申请日：2009-06-15
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： F02C6/08 , F02C7/12
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。

2. 发明授权

US08336206B1 Process of forming a high temperature turbine rotor blade 有权
标题翻译：形成高温涡轮转子叶片的工艺
公开(公告)号：US08336206B1
公开(公告)日：2012-12-25
申请号：US13157364
申请日：2011-06-10
申请人： Wesley D Brown , William L Plank
发明人： Wesley D Brown , William L Plank
IPC分类号： B21D53/78 , B63H1/26
CPC分类号： F01D5/28 , F01D5/18 , Y10T29/49332 , Y10T29/49336 , Y10T29/49337
摘要： A turbine rotor blade made from the spar and shell construction in which the shell formed from a plurality of shell segments each being a thin wall shell segment made from a high temperature resistant material that is formed by a wire EDM process, and where the shell segments are each secured to the spar separately using a retainer that is poured into retainer occupying spaces formed in the shell segments and the spar, and then hardened to form a rigid retainer to secure each shell segment to the spar individually. The spar includes a number of radial extending projections each with a row of cavities that form the retainer occupying spaces in order to spread the loads around. The retainer can be a bicast material, a transient liquid phase bonding material, or a sintered metal. An old shell can be easily removed and replaced with a new shell by removing parts of the retainer and re-pouring a new retainer with a new shell in place.
摘要翻译：一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体由多个壳段形成，每个壳段均由由电线EDM工艺形成的耐高温材料制成的薄壁壳段，并且其中壳段各自使用保持器分别固定到翼梁上，该保持器被注入到形成在壳段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，以将每个壳段单独地固定到翼梁。翼梁包括多个径向延伸的突起，每个具有一排空腔，形成保持器占据空间，以便使负载周围扩展。保持器可以是组播材料，瞬态液相粘合材料或烧结金属。可以通过移除保持器的部件并将新的保持器重新装入新的壳体中，可以容易地移除旧壳体并用新的壳体代替。

3. 发明授权

US08475112B1 Multiple staged compressor with last stage airfoil cooling 有权
标题翻译：多级压缩机，最后阶段翼型冷却
公开(公告)号：US08475112B1
公开(公告)日：2013-07-02
申请号：US13526601
申请日：2012-06-19
申请人： John E Ryznic , Wesley D Brown
发明人： John E Ryznic , Wesley D Brown
IPC分类号： F01D5/14 , F03B11/00 , F03D11/00 , F04D29/38
CPC分类号： F02C6/08 , F02C7/18 , F04D29/324 , F04D29/542 , F04D29/5826 , F04D29/584 , F05D2260/205 , F05D2260/208 , Y02T50/676
摘要： A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by drawing heat away from the airfoils using a heat pipe, and then passing cooling air through a heat exchanger associated with the heat pipe to draw heat away from the heat pipe. The cooling air used for cooling the airfoils is bled off from an earlier stage than the last stage and then discharged into a stage upstream from the bleed off location.
摘要翻译：具有多级翼型件以产生高压口径的高压缩比压缩机，其中最后一级机翼通过使用热管从翼型件中抽出热而冷却，然后使冷却空气通过与热管相关联的热交换器将热量从热管中吸走。用于冷却翼型的冷却空气从比最后阶段更早的阶段排出，然后排放到排放位置上游的阶段。

4. 发明授权

US08382439B1 Process of forming a high temperature turbine rotor blade 有权
标题翻译：形成高温涡轮转子叶片的工艺
公开(公告)号：US08382439B1
公开(公告)日：2013-02-26
申请号：US13244335
申请日：2011-09-24
申请人： Wesley D Brown
发明人： Wesley D Brown
IPC分类号： B23K5/18
CPC分类号： F01D5/188 , F01D5/147 , Y10T29/49341 , Y10T29/49343
摘要： 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.
摘要翻译：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。

5. 发明授权

US09394799B1 Air riding seal for a turbine 有权
标题翻译：涡轮机用空气密封
公开(公告)号：US09394799B1
公开(公告)日：2016-07-19
申请号：US14795095
申请日：2015-07-09
申请人： Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
发明人： Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
IPC分类号： F16J15/34 , F01D11/02
CPC分类号： F01D11/025 , F01D11/003 , F16J15/34 , F16J15/3448
摘要： 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.
摘要翻译：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。

6. 发明授权

US08052391B1 High temperature turbine rotor blade 有权
标题翻译：高温涡轮转子叶片
公开(公告)号：US08052391B1
公开(公告)日：2011-11-08
申请号：US12410489
申请日：2009-03-25
申请人： Wesley D Brown
发明人： Wesley D Brown
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/147 , Y10T29/49341 , Y10T29/49343
摘要： 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.
摘要翻译：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。

7. 发明授权

US07670116B1 Turbine vane with spar and shell construction 有权
标题翻译：涡轮叶片与翼梁和壳结构
公开(公告)号：US07670116B1
公开(公告)日：2010-03-02
申请号：US11243308
申请日：2005-10-04
申请人： Jack W. Wilson, Jr. , Wesley D Brown
发明人： Jack W. Wilson, Jr. , Wesley D Brown
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/189 , F01D5/20 , Y10T29/49327 , Y10T29/49339 , Y10T29/49341
摘要： 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.
摘要翻译：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。

8. 发明授权

US10024170B1 Integrally bladed rotor with bore entry cooling holes 有权
公开(公告)号：US10024170B1
公开(公告)日：2018-07-17
申请号：US15203905
申请日：2016-07-07
申请人： Robert L Memmen , Wesley D Brown
发明人： Robert L Memmen , Wesley D Brown
IPC分类号： F01D5/18 , F01D5/08
摘要： 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.

9. 发明授权

US08070450B1 High temperature turbine rotor blade 有权
标题翻译：高温涡轮转子叶片
公开(公告)号：US08070450B1
公开(公告)日：2011-12-06
申请号：US12426343
申请日：2009-04-20
申请人： John E Ryznic , Wesley D Brown
发明人： John E Ryznic , Wesley D Brown
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F05D2300/13 , F05D2300/131
摘要： A turbine rotor blade made from the spar and shell construction in which the shell formed from a plurality of shell segments each being a thin wall shell segment made from a high temperature resistant material that is formed by a wire EDM process, and where the shell segments are each secured to the spar separately using a retainer that is poured into retainer occupying spaces formed in the shell segments and the spar, and then hardened to form a rigid retainer to secure each shell segment to the spar individually. The spar includes a number of radial extending projections each with a row of cavities that form the retainer occupying spaces in order to spread the loads around. The retainer can be a bicast material, a transient liquid phase bonding material, or a sintered metal. An old shell can be easily removed and replaced with a new shell by removing parts of the retainer and re-pouring a new retainer with a new shell in place.
摘要翻译：一种由翼梁和壳体结构制成的涡轮转子叶片，其中壳体由多个壳段形成，每个壳段均由由电线EDM工艺形成的耐高温材料制成的薄壁壳段，并且其中壳段各自使用保持器分别固定到翼梁上，该保持器被注入到形成在壳段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，以将每个壳段单独地固定到翼梁。翼梁包括多个径向延伸的突起，每个具有一排空腔，形成保持器占据空间，以便使负载周围扩展。保持器可以是组播材料，瞬态液相粘合材料或烧结金属。可以通过移除保持器的部件并将新的保持器重新装入新的壳体中，可以容易地移除旧壳体并用新的壳体代替。

10. 发明授权

US08015705B2 Spar and shell blade with segmented shell 有权
公开(公告)号：US08015705B2
公开(公告)日：2011-09-13
申请号：US12843935
申请日：2010-07-27
申请人： Jack W Wilson, Jr. , Wesley D Brown
发明人： Jack W Wilson, Jr. , Wesley D Brown
IPC分类号： F01D5/18
CPC分类号： F01D5/147 , F01D5/189 , F01D5/20 , Y10T29/49327 , Y10T29/49339 , Y10T29/49341
摘要： A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell half is radially loaded by an attachment so that its load is not carried by the upper shell half and the tip of the spar in order to reduce overall stress levels.

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