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1. 发明申请

US20140230441A1 HEAT SHIELD MANIFOLD SYSTEM FOR A MIDFRAME CASE OF A GAS TURBINE ENGINE 有权
标题翻译：用于燃气轮机发动机的壳体散热器散热系统
公开(公告)号：US20140230441A1
公开(公告)日：2014-08-21
申请号：US13768038
申请日：2013-02-15
申请人： Clinton A. Mayer , Jesse Eng , Cheryl A. Schopf
发明人： Clinton A. Mayer , Jesse Eng , Cheryl A. Schopf
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D25/26 , F05D2260/231
摘要： A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.
摘要翻译：公开了一种用于压缩机和涡轮机组件之间的内壳的隔热罩歧管系统。隔热罩歧管系统保护外壳免受高温压缩机排放空气的影响，从而使压缩机和涡轮机组件之间延伸的外壳由不需要的材料形成。此外，隔热罩歧管系统可以被配置成使得压缩机排出的空气从压缩机传递到隔热管歧管系统中，而不会通过常规的法兰到容易泄漏的法兰接头。

2. 发明授权

US09714611B2 Heat shield manifold system for a midframe case of a gas turbine engine 有权
公开(公告)号：US09714611B2
公开(公告)日：2017-07-25
申请号：US13768038
申请日：2013-02-15
申请人： Clinton A. Mayer , Jesse Eng , Cheryl A. Schopf
发明人： Clinton A. Mayer , Jesse Eng , Cheryl A. Schopf
IPC分类号： F02C7/12 , F01D25/26
CPC分类号： F02C7/12 , F01D25/26 , F05D2260/231
摘要： A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.

3. 发明申请

US20140205447A1 PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY 有权
标题翻译：用于燃气涡轮机组件排气部分的冲洗和冷却空气
公开(公告)号：US20140205447A1
公开(公告)日：2014-07-24
申请号：US13746486
申请日：2013-01-22
申请人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
发明人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
IPC分类号： F02C7/18 , F01D25/16 , F02C6/08
CPC分类号： F02C7/18 , F01D9/02 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F02C6/08 , F05D2240/15
摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
摘要翻译：具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流空气从外部流路壁向径向外侧排出到排气套管腔的位置。

4. 发明授权

US07658588B1 Optimized blade tip clearance process for a rub tolerant design 有权
标题翻译：优化刀片间隙过程，实现耐磨设计
公开(公告)号：US07658588B1
公开(公告)日：2010-02-09
申请号：US11698382
申请日：2007-01-26
申请人： Cheryl A. Schopf , Jack W. Wilson, Jr.
发明人： Cheryl A. Schopf , Jack W. Wilson, Jr.
IPC分类号： F01D11/08
CPC分类号： F01D21/003 , F01D11/08 , F01D11/14 , F05D2230/50 , F05D2240/11 , F05D2260/80
摘要： A process for optimizing a blade tip clearance for a rub tolerate design in a gas turbine engine that includes evaluating a selection of candidate materials for galling and heat generation, selecting a subset of the candidate materials and analyze engine transient tip clearance for the subset materials, verifying the optimum material cooling and heat shielding for tip clearance and structures, and analyze and select an engine break-in procedure for the optimum tip clearance between turbine and compressor. If one of the subset materials results in a poor performance, than another material from the candidate materials is selected and reanalyzed until the best materials have been found. When the best materials are found, then a finite element method of analysis is performed from the blade and the static parts that form the tip clearance is performed to evaluate the materials for damage. If required, the blade and tip squealer configuration is altered to reduce stress, or blade tip coating is used. If a micro-crack in the static part will propagate, then the configuration of the hooks, scallops and the part thickness is reconfigured to reduce stress. Then, a #D analysis is performed for out-of-roundness, centerline bending and rotor sag. The design configuration and manufacturing is reiterated in order to optimize out-of-roundness.
摘要翻译：一种用于优化用于燃气涡轮发动机中的耐磨设计的叶片顶端间隙的方法，其包括评估用于磨损和产生热量的候选材料的选择，选择所述候选材料的子集并分析所述子集材料的发动机瞬态尖端间隙，验证顶端间隙和结构的最佳材料冷却和热屏蔽，并分析和选择用于涡轮机和压缩机之间的最佳顶端间隙的发动机启动程序。如果子集中的一个材料导致性能不佳，则选择和重新分析来自候选材料的另一种材料，直到找到最佳材料。当找到最好的材料时，从叶片进行有限元分析方法，并执行形成顶端间隙的静态部件，以评估材料的损坏。如果需要，刀片和尖端尖叫机配置被改变以减少应力，或者使用刀尖涂层。如果静态部分的微裂纹会传播，则重新配置钩，扇贝和部件厚度的配置以减轻应力。然后，对于不圆度，中心线弯曲和转子下垂进行#D分析。重申设计配置和制造，以优化不圆度。

5. 发明授权

US09316153B2 Purge and cooling air for an exhaust section of a gas turbine assembly 有权
标题翻译：用于燃气轮机组件的排气部分的吹扫和冷却空气
公开(公告)号：US09316153B2
公开(公告)日：2016-04-19
申请号：US13746486
申请日：2013-01-22
申请人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
发明人： Harry Patat , Cheryl A. Schopf , Jerome H. Katy , Adam Wallace , David J. Wiebe
IPC分类号： F01D25/12 , F01D9/02 , F01D9/06 , F01D25/16 , F01D25/30 , F02C6/08 , F02C7/18
CPC分类号： F02C7/18 , F01D9/02 , F01D9/065 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F02C6/08 , F05D2240/15
摘要： A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall.
摘要翻译：具有外壳，内壳，限定在外流路壁和内流路壁之间的环形排气通道的涡轮机排气外壳以及从气体路径径向向外和径向向内定位的涡轮排气壳体腔。多个结构支柱将内壳支撑到外壳，并且整流罩围绕在外流路壁和内流路壁之间延伸的区域中的每个支柱。第一吹扫空气路径延伸穿过支柱中的至少一个，用于将吹扫冷却空气径向向内引导到内部壳体，并且第二吹扫空气路径延伸穿过支柱，以进一步将吹扫冷却空气径向向外引导以提供吹扫流空气从外部流路壁向径向外侧排出到排气套管腔的位置。

6. 发明授权

US07748209B1 Small single use gas turbine engine with oil-less bearing arrangement 有权
标题翻译：小型单用燃气轮机，无油轴承装置
公开(公告)号：US07748209B1
公开(公告)日：2010-07-06
申请号：US11636273
申请日：2006-12-08
申请人： Cheryl A. Schopf , Jack W. Wilson, Jr. , Wesley Brown
发明人： Cheryl A. Schopf , Jack W. Wilson, Jr. , Wesley Brown
IPC分类号： F02C7/06
CPC分类号： F02C9/18 , F01D5/082 , F01D25/125 , F02C7/06 , F05D2260/201 , F05D2260/221 , F16C19/163 , F16C19/542 , F16C37/007 , Y02T50/671 , Y02T50/676
摘要： A small single use gas turbine engine with a twin spool rotor shaft and a bypass fan, the rotor shafts being supported for rotation by bearings in the front and rear compartments of the engine. A portion of the bypass fan air is diverted to flow through the bearings in order to provide for cooling of the high speed bearings. Because a large amount of cooling air is required to cool the bearings, an air in tube is positioned in each of the guide vanes in the turbine section to provide for a cooling air passage leading into the rear bearings. In the front bearings, cooling air from the bypass fan is bled off from a location just upstream from the entrance to the centrifugal compressor. A fuel mist tube supplies fuel mist to the cooling air before passing through the bearings to provide extra cooling for the bearings and to provide lubrication to improve the service life of the engine. Because the cooling air is supplied by the bypass fan, the pressure is high enough and the volume is large enough to provide adequate cooling for the high rotational speed bearings used in such a small and high rotating gas turbine engine.
摘要翻译：具有双卷轴转子轴和旁通风扇的小型单次使用燃气涡轮发动机，转子轴由发动机的前后隔室中的轴承支撑以转动。旁路风扇空气的一部分被转向流过轴承，以便提供高速轴承的冷却。由于需要大量的冷却空气来冷却轴承，所以在涡轮机部分的每个导向叶片中定位管中的空气以提供通向后轴承的冷却空气通道。在前轴承中，来自旁路风扇的冷却空气从入口到离心式压缩机的上游位置排出。燃料雾管在通过轴承之前向冷却空气提供燃料雾以为轴承提供额外的冷却并提供润滑以提高发动机的使用寿命。由于冷却空气由旁通风扇提供，所以压力足够高，并且体积足够大以为用于这种小型和高旋转燃气涡轮发动机的高转速轴承提供足够的冷却。

7. 发明授权

US07748952B1 Snorkel tube for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的浮潜管
公开(公告)号：US07748952B1
公开(公告)日：2010-07-06
申请号：US12184885
申请日：2008-08-01
申请人： Cheryl A. Schopf , Jack W. Wilson, Jr.
发明人： Cheryl A. Schopf , Jack W. Wilson, Jr.
IPC分类号： F01D25/12
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： A small twin spool gas turbine engine with a bearing support arrangement in which the bearings are dampened by O-rings secured between the bearing races and the support structure, and in which the bearings are arranged in series so that a cooling air can be passed through the bearings to prevent overheating. The aft end of the engine includes high speed and low speed ball bearings supported with preload springs to add additional damping capability. The fore and aft end bearing support assemblies forms a cooling air path for the cooling fluid to flow through a passage within one of the guide vanes, through the bearings and out through a hole in the low pressure turbine rotor disk. the bearing cooling air passage includes a snorkel tube that extends from a guide vane cooling air passage and into the bypass air channel to draw in the cooling air used for the bearings. The snorkel tube includes a slanted opening so that dirt particulates do not enter the bearing cooling air passage.
摘要翻译：一种具有轴承支撑装置的小型双阀芯燃气涡轮发动机，其中轴承被固定在轴承座和支撑结构之间的O形环夯实，并且其中轴承串联布置，使得冷却空气可以通过轴承防止过热。发动机的后端包括用预加载弹簧支撑的高速和低速球轴承，以增加额外的阻尼能力。前端和后端轴承支撑组件形成冷却空气路径，用于冷却流体流过一个导叶内的通道，穿过轴承并通过低压涡轮转子盘中的孔流出。轴承冷却空气通道包括从引导叶片冷却空气通道延伸到旁通空气通道中以吸入用于轴承的冷却空气中的吸管。浮潜管包括倾斜开口，使得污垢颗粒不进入轴承冷却空气通道。

8. 发明授权

US06805533B2 Tolerant internally-cooled fluid guide component 有权
标题翻译：耐受内冷流体导向组件
公开(公告)号：US06805533B2
公开(公告)日：2004-10-19
申请号：US10256798
申请日：2002-09-27
申请人： Cheryl A. Schopf
发明人： Cheryl A. Schopf
IPC分类号： F01D518
CPC分类号： F01D5/189 , F05D2260/201
摘要： A cooled fluid flow component for a combustion engine which employs internal impingement and exterior surface film cooling is disclosed. The fluid flow component has improved tolerance to assembly and manufacturing variations. The fluid flow component includes at least one interior cavity having an associated impingement sleeve. An impingement annulus surrounding the impingement sleeve is divided into more than one region, with each region forced to have a pressure equal, pressure, with the pressure induced being sufficient to provide adequate backflow margin. The external cooling holes are shaped to address possible overflow tendencies, and the impingement holes are adapted to reduce or eliminate possible losses of impingement cooling effectiveness.
摘要翻译：公开了一种采用内部冲击和外表面薄膜冷却的用于内燃机的冷却流体流动部件。流体流动部件具有改进的对组装和制造变化的耐受性。流体流动部件包括至少一个具有相关联的冲击套管的内腔。围绕冲击套筒的冲击环被分成多于一个区域，每个区域被迫使压力等于压力，压力足以提供足够的回流余量。外部冷却孔的形状是为了解决可能的溢出趋势，并且冲击孔适于减少或消除冲击冷却效果的可能损失。

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