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公开(公告)号：US20170159484A1
公开(公告)日：2017-06-08
申请号：US15237211
申请日：2016-08-15
IPC分类号： F01D17/02
CPC分类号： F01D17/02 , F01D5/26 , F05D2260/12 , F05D2260/80 , F05D2260/83 , F05D2260/961 , G01P5/165 , Y02T50/671 , Y02T50/673
摘要： An annular air flow passage, particularly for a turbine engine, comprising two radially internal and external annular walls, wherein an element is elongated in a direction between the internal and external annular walls and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. According to the invention, the annular flow passage comprises means of variation, along said direction, of the center of gravity position of the element.
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公开(公告)号：US09670793B2
公开(公告)日：2017-06-06
申请号：US14255991
申请日：2014-04-18
申请人： Siemens Energy, Inc.
发明人： Paul J. Zombo
CPC分类号： F01D17/085 , F01D21/003 , F05D2260/80 , F05D2260/83 , F05D2270/80 , G01N25/72
摘要： A thermal imaging system that detects the growth of cracks in a structural element, where the system has particular application for detecting the growth of cracks and similar defects in a turbine blade. The thermal imaging system includes at least one infrared (IR) fiber optic cable where a sensing end of the fiber optic cable is positioned in close proximity to a location where a crack in the structural element may occur. Infrared emissions generated as a result of crack growth are collected by the IR fiber cable and transmitted by the cable to an infrared monitoring device. The amount of heat that is detected provides an indication of whether the crack is growing, and if so, at what rate.
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公开(公告)号：US09654161B2
公开(公告)日：2017-05-16
申请号：US15200102
申请日：2016-07-01
IPC分类号： G01M15/14 , H04B1/16 , G01M17/007 , F02C6/16 , G01M9/02
CPC分类号： H04B1/1646 , B65D19/16 , F01D5/02 , F01D17/02 , F01D21/003 , F01D25/285 , F02C6/16 , F04D27/001 , F04D29/321 , F05B2220/302 , F05B2260/83 , F05D2220/323 , F05D2260/83 , F23R2900/00019 , G01M9/02 , G01M9/04 , G01M15/14 , G01M17/007 , Y02E60/15
摘要： A process for testing a turbine of a gas turbine engine at high altitudes, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.
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公开(公告)号：US09645050B2
公开(公告)日：2017-05-09
申请号：US14638569
申请日：2015-03-04
申请人： ROLLS-ROYCE PLC
发明人： Peter Allford
IPC分类号： G01M15/14 , F01D21/00 , F04D27/00 , F04D27/02 , F04D29/56 , F01D25/28 , G01M13/02 , F01D17/16
CPC分类号： G01M15/14 , F01D17/16 , F01D21/003 , F01D25/285 , F04D27/001 , F04D27/0246 , F04D29/563 , F05D2260/83 , G01M13/027
摘要： An apparatus for investigating mechanical operational characteristics of a gas turbine variable vane actuation system includes coaxial inner and outer annular casings corresponding to inner and outer casings of a gas turbine engine. The apparatus includes a circumferential row of vane substitutes, each extending between an inner end at the inner casing and an outer end at the outer casing, and rotatable about an axis extending through its ends to emulate the rotation of a variable vane in the engine. The apparatus includes respective loading devices for the vane substitutes, each applying a mechanical load to its vane substitute between the inner and outer ends as the vane substitute rotates to emulate the aerodynamic loading on a variable vane in the engine and to generate resulting frictional loading at the inner and outer ends which emulates resulting the frictional loading at the ends of the variable vane in the engine.
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公开(公告)号：US20170115183A1
公开(公告)日：2017-04-27
申请号：US15287459
申请日：2016-10-06
申请人： ROLLS-ROYCE plc
发明人： Stefano BIANCHI , Howoong NAMGOONG
CPC分类号： G01M15/14 , F01D17/08 , F05D2260/12 , F05D2260/83 , G01F1/684 , G01F15/18 , G01P5/02 , G01P5/10 , G01P5/12
摘要： A sensor system is disclosed comprising a sensor and a mast on which the sensor is mounted. The mast comprises a core body and a shroud, whereby the shroud is provided about the core body and the shroud is rotatable with respect to the core body under the influence, in use, of a fluid flow flowing past the shroud. The shroud is shaped so as, from at least one fluid flow direction, it presents a different flow resistance in dependence upon its rotational orientation. The rotational orientation of the shroud adjusts to reduce the flow resistance produced by the shroud to the fluid flow in response to the commencement of, or a change in the fluid flow direction to, one of the at least one fluid flow directions.
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46.发明申请公开(公告)号：US20170107859A1
公开(公告)日：2017-04-20
申请号：US15392028
申请日：2016-12-28
申请人： ROLLS-ROYCE plc
发明人： Daniel CLARK , Justin BURROWS , James KELL
IPC分类号： F01D25/28 , F01D25/00 , F01D9/02 , G02B23/24 , B23Q17/24 , F16L3/02 , F16M13/02 , F01D5/00 , B23Q9/00
CPC分类号： F01D25/285 , B23Q9/0042 , B23Q17/2409 , F01D5/005 , F01D9/02 , F01D9/065 , F01D21/003 , F01D25/002 , F05D2230/72 , F05D2240/14 , F05D2260/83 , F16L3/01 , F16L3/02 , F16M13/02 , F16M13/022 , G02B23/2476 , Y10T29/49318 , Y10T29/49826
摘要： An apparatus for supporting a tool in an assembled apparatus. The apparatus includes a support structure, the support structure having a central member and a plurality of support members pivotally mounted on the central member. The support members are movable between a non-deployed position in which the support members extend a minimum distance from the central member and a deployed position in which the support members extend a maximum distance from the central member.
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公开(公告)号：US20170101883A1
公开(公告)日：2017-04-13
申请号：US15381825
申请日：2016-12-16
IPC分类号： F01D11/12 , C23C4/134 , B05D5/06 , B05D7/14 , C23C28/04 , F01D5/28 , F01D9/02 , C04B35/50 , C04B35/622 , C04B41/50 , C04B41/52 , C04B41/87 , C04B41/89 , C04B41/00 , C23C4/10
CPC分类号： F01D11/122 , B05D1/36 , B05D5/061 , B05D7/14 , B32B18/00 , C04B35/50 , C04B35/62222 , C04B41/009 , C04B41/5024 , C04B41/52 , C04B41/85 , C04B41/87 , C04B41/89 , C04B2111/807 , C23C4/04 , C23C4/067 , C23C4/10 , C23C4/134 , C23C14/06 , C23C14/14 , C23C16/22 , C23C16/24 , C23C28/04 , C23C28/044 , C23C28/321 , C23C28/34 , C23C28/345 , F01D5/288 , F01D9/02 , F05D2220/32 , F05D2230/312 , F05D2260/83 , F05D2300/211 , G01B11/0616 , C04B35/14 , C04B35/565 , C04B35/584 , C04B35/10 , C04B35/18 , C04B20/0036 , C04B41/4527 , C04B41/4582 , C04B2103/0021 , C04B41/524
摘要： In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer.
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公开(公告)号：US20170097284A1
公开(公告)日：2017-04-06
申请号：US15200102
申请日：2016-07-01
CPC分类号： H04B1/1646 , B65D19/16 , F01D5/02 , F01D17/02 , F01D21/003 , F01D25/285 , F02C6/16 , F04D27/001 , F04D29/321 , F05B2220/302 , F05B2260/83 , F05D2220/323 , F05D2260/83 , F23R2900/00019 , G01M9/02 , G01M9/04 , G01M15/14 , G01M17/007 , Y02E60/15
摘要： A process for testing a turbine of a gas turbine engine at high altitudes, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.
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公开(公告)号：US20170097283A1
公开(公告)日：2017-04-06
申请号：US15200057
申请日：2016-07-01
CPC分类号： H04B1/1646 , B65D19/16 , F01D5/02 , F01D17/02 , F01D21/003 , F01D25/285 , F02C6/16 , F04D27/001 , F04D29/321 , F05B2220/302 , F05B2260/83 , F05D2220/323 , F05D2260/83 , F23R2900/00019 , G01M9/02 , G01M9/04 , G01M15/14 , G01M17/007 , Y02E60/15
摘要： A process for testing a combustor of a gas turbine engine, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the combustor to produce a decreased pressure such that a low atmospheric condition at the combustor exit is simulated.
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公开(公告)号：US20170097234A1
公开(公告)日：2017-04-06
申请号：US15387944
申请日：2016-12-22
CPC分类号： G01B21/32 , C23C4/11 , C23C24/04 , F01D17/04 , F05D2230/31 , F05D2260/80 , F05D2260/83 , F05D2270/808 , G01B11/165 , G01L1/2287 , G01M5/0016 , G01M5/0041 , G01M15/14
摘要： Methods for manufacturing passive strain indicator on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points.
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