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1. 发明申请

US20180171811A1 EXPANSION MACHINE HAVING A SHAFT SEALING RING AND A VALVE 审中-公开
公开(公告)号：US20180171811A1
公开(公告)日：2018-06-21
申请号：US15539102
申请日：2015-10-22
申请人： Robert Bosch GmbH
发明人： Nadja Eisenmenger , Steffen Buhl
IPC分类号： F01D11/00 , F01D11/02 , F01D5/04
CPC分类号： F01D11/003 , F01D5/046 , F01D11/001 , F01D11/02
摘要： The invention relates to an expansion machine (20), comprising an output shaft (24) and a shaft sealing ring (25) that interacts with the output shaft. The expansion machine (20) has an inflow region (21) and an outflow region (22). During operation, a working medium flows through the expansion machine (20), wherein compressed working medium flows into the inflow region (21) and expanded working medium flows out of the outflow region (22). The shaft sealing ring (25) separates a valve space (11) filled with working medium from a surrounding space (40). A valve (10) is arranged in the expansion machine (20). The pressure in the valve space (11) can be controlled by means of the valve (10).

2. 发明授权

US09879603B2 Axial flow machine cooling system 有权
公开(公告)号：US09879603B2
公开(公告)日：2018-01-30
申请号：US14458593
申请日：2014-08-13
申请人： ROLLS-ROYCE PLC
发明人： Alan Robert Maguire , Timothy John Scanlon , Colin Young
IPC分类号： F02C7/18 , F01D5/08 , F02C6/08 , F01D5/04 , F01D9/06 , F01D25/08 , F02C7/12 , F01D25/12 , F02C3/00
CPC分类号： F02C7/18 , F01D5/046 , F01D5/08 , F01D5/081 , F01D5/082 , F01D9/06 , F01D25/08 , F01D25/12 , F02C3/00 , F02C6/08 , F02C7/12 , F05D2220/32 , F05D2260/20 , F05D2260/205 , Y02T50/676
摘要： This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.

3. 发明授权

US09835036B2 Compressor wheel 有权
公开(公告)号：US09835036B2
公开(公告)日：2017-12-05
申请号：US14558693
申请日：2014-12-02
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： Christian Holzschuh , Andreas Haas , Martin Schlegl , Christian Peschke
IPC分类号： F01D5/28 , F01D5/04 , B23P15/00
CPC分类号： F01D5/288 , B23P15/006 , F01D5/046 , F05D2220/40 , Y10T29/49321 , Y10T29/49337
摘要： A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.

4. 发明申请

US20170248152A1 ROTOR WHEEL AND IMPELLER INSERTS 审中-公开
公开(公告)号：US20170248152A1
公开(公告)日：2017-08-31
申请号：US15052973
申请日：2016-02-25
申请人： General Electric Company
发明人： Kiran Sreeram , John Herbert Dimmick, III , Gary Charles Liotta , John Robert Sech , Eric Richard Bonini , Patrick Shawn Reilly
IPC分类号： F04D29/32 , F04D29/52 , F01D25/12 , F04D29/64
CPC分类号： F04D29/322 , F01D5/046 , F01D5/048 , F01D5/087 , F01D5/187 , F01D5/188 , F01D25/12 , F04D29/522 , F04D29/644 , F05D2220/32 , F05D2230/10 , F05D2230/232 , F05D2260/30 , F05D2260/60 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

5. 发明授权

US09657746B2 Compressor rotor with anti-vortex fins 有权
公开(公告)号：US09657746B2
公开(公告)日：2017-05-23
申请号：US14472958
申请日：2014-08-29
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Tibor Urac
IPC分类号： F04D29/32 , F04D29/28 , F01D5/04 , F02C6/08
CPC分类号： F04D29/667 , F01D5/045 , F01D5/046 , F02C6/08 , F04D29/284 , F04D29/321
摘要： A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented.

6. 发明申请

US20170089263A1 TURBINE ENGINE ADVANCED COOLING SYSTEM 审中-公开
公开(公告)号：US20170089263A1
公开(公告)日：2017-03-30
申请号：US14871382
申请日：2015-09-30
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
发明人： Joseph Clegg , Craig English , Behram Kapadia , Kenneth M. Pesyna , Jason Lee Swindle , Jason Wayne Rector , Christopher Vincent , Nicholas D. Metzger , Daniel G. Edwards
IPC分类号： F02C7/12 , F02C7/24 , F04D29/58 , F01D25/12 , F04D29/32 , F02C3/04 , F01D5/02
CPC分类号： F02C7/12 , F01D5/02 , F01D5/046 , F01D5/08 , F01D5/081 , F01D5/082 , F01D25/08 , F01D25/12 , F02C3/04 , F02C6/08 , F02C7/18 , F02C7/185 , F02C7/24 , F04D29/321 , F04D29/582 , F05D2220/32 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/60 , F05D2260/14 , F05D2260/20 , F05D2260/205 , F05D2260/231
摘要： A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

7. 发明授权

US09476305B2 Impingement-cooled turbine rotor 有权
标题翻译：冲击式涡轮转子
公开(公告)号：US09476305B2
公开(公告)日：2016-10-25
申请号：US13892828
申请日：2013-05-13
申请人： HONEYWELL INTERNATIONAL INC.
发明人： David K. Jan , Amandine Miner
IPC分类号： F01D5/08 , F01D5/30 , F01D5/04 , F01D5/18
CPC分类号： F01D5/081 , F01D5/045 , F01D5/046 , F01D5/087 , F01D5/187 , F01D5/3061 , F05D2240/81 , F05D2260/201 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.
摘要翻译：整体涡轮机包括前轮毂部分和后轮毂部分。前轮毂部分和后轮毂部分沿着环形接口彼此冶金地联接，该环形接口位于大致垂直于轴向分离的涡轮机的旋转轴线的平面内。涡轮进一步包括翼形叶片环，该叶片环冶金地联接到所耦合的前和后轮毂部分的径向外表面，以及形成在所耦合的前部和后部毂部分的内部部分内的冲击腔。冲击腔包括内接表面，该内表面靠近所耦合的前后轮毂段的径向外表面。此外，冲击冷却空气流撞击冲击腔的内表面，以向耦合的前和后毂部分的径向外表面提供对流和导电冷却。

8. 发明申请

US20150308342A1 GAS TURBINE ENGINE VAPOR COOLED CENTRIFUGAL IMPELLER 审中-公开
标题翻译：燃气涡轮发动机蒸汽冷却离心式叶轮
公开(公告)号：US20150308342A1
公开(公告)日：2015-10-29
申请号：US14524736
申请日：2014-10-27
申请人： United Technologies Corporation
发明人： James W. Norris
IPC分类号： F02C7/16 , F01D5/08 , F02C3/04 , F01D25/16 , F01D5/02 , F01D1/02 , F01D25/12
CPC分类号： F02C7/16 , F01D5/045 , F01D5/046 , F01D5/088 , F01D5/181 , F04D29/285 , F04D29/584 , F05D2260/207 , F05D2260/208 , F05D2260/2322
摘要： A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
摘要翻译：燃气涡轮发动机径向叶轮包括沿着径向叶轮的中性弯曲平面彼此固定的第一和第二叶轮部分。蒸气冷却腔设置在第一和第二叶轮部分之间。中性弯曲平面布置在蒸气冷却腔中。

9. 发明申请

US20150152740A1 COMPRESSOR WHEEL 有权
标题翻译：压缩机轮
公开(公告)号：US20150152740A1
公开(公告)日：2015-06-04
申请号：US14558693
申请日：2014-12-02
申请人： Bosch Mahle Turbo Systems GmbH & Co. KG
发明人： Christian Holzschuh , Andreas Haas , Martin Schlegl , Christian Peschke
IPC分类号： F01D5/28 , F02B39/16 , B23P15/02
CPC分类号： F01D5/288 , B23P15/006 , F01D5/046 , F05D2220/40 , Y10T29/49321 , Y10T29/49337
摘要： A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.
摘要翻译：用于内燃机的压缩机叶轮可以包括在轮的圆周方向上彼此间隔开的多个叶片。多个叶片可以分别包括流入边缘，其在操作期间受到可压缩流体基本轴向地流入轮轴。多个叶片可以包括局部不同材料的表面层，以在操作期间适应局部不同的载荷。

10. 发明授权

US09033670B2 Axially-split radial turbines and methods for the manufacture thereof 有权
标题翻译：轴向分裂的径向涡轮机及其制造方法
公开(公告)号：US09033670B2
公开(公告)日：2015-05-19
申请号：US13444070
申请日：2012-04-11
申请人： Don Mittendorf , David K. Jan , Jason Smoke , Amandine Miner
发明人： Don Mittendorf , David K. Jan , Jason Smoke , Amandine Miner
IPC分类号： F01D5/04 , F01D5/18 , F01D5/30 , B23P15/00
CPC分类号： F01D5/147 , B23P15/006 , F01D5/04 , F01D5/045 , F01D5/046 , F01D5/048 , F01D5/066 , F01D5/088 , F01D5/18 , F01D5/187 , F01D5/28 , F01D5/30 , F05D2230/60 , Y02T50/671 , Y02T50/676 , Y10T29/49321 , Y10T29/49323 , Y10T29/49341
摘要： Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.
摘要翻译：轴向分离的径向涡轮机的实施例，如用于制造轴向分离的径向涡轮机的方法的实施例。在一个实施例中，该方法包括以下步骤：将前叶片环连接到前盘，以产生正向涡轮转子，制造后涡轮转子，以及将正向涡轮转子和后涡轮转子设置在轴向邻接的旋转固定关系以产生轴向分离的径向涡轮机。

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