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公开(公告)号：US20180171819A1
公开(公告)日：2018-06-21
申请号：US15818968
申请日：2017-11-21
申请人： ROLLS-ROYCE plc
发明人： Paul M. HIELD
IPC分类号： F01D17/16
CPC分类号： F01D17/162 , F01D5/145 , F01D5/146 , F04D29/563 , F05D2240/123 , F05D2240/124 , Y02T50/673
摘要： There is disclosed a variable guide vane device for a gas turbine engine comprising first and second vanes arranged in axial flow series. The first and second vanes are spaced apart so as to define a radially extending slot for fluid flow therebetween.
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公开(公告)号：US09957824B2
公开(公告)日：2018-05-01
申请号：US14776473
申请日：2014-03-14
发明人： Carl Brian Klinetob , Stephen J. Lindahl , Myron L. Klein , Andrew Pope , William Richard Ganoe, Jr. , Thomas D. Kasprow , Douglas J. Morgan
CPC分类号： F01D9/041 , F01D5/16 , F01D5/26 , F01D25/06 , F05D2230/60 , F05D2240/12 , F05D2240/123 , F05D2240/124 , F05D2260/96 , F05D2300/121 , F05D2300/171
摘要： A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.
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公开(公告)号：US09945325B2
公开(公告)日：2018-04-17
申请号：US14646990
申请日：2013-11-06
发明人： Gary D. Roberge
CPC分类号： F02K3/115 , F01D9/065 , F02C7/06 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/105 , F05D2210/12 , F05D2240/123 , F05D2240/124 , F05D2250/182 , F05D2250/60 , F05D2260/20 , F05D2260/213 , F05D2260/4031 , F05D2260/98 , Y02T50/676
摘要： An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.
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公开(公告)号：US20180094643A1
公开(公告)日：2018-04-05
申请号：US15286545
申请日：2016-10-05
CPC分类号： F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180087529A1
公开(公告)日：2018-03-29
申请号：US15278994
申请日：2016-09-28
发明人： Moorthi Subramaniyan , Sagar Kamble
CPC分类号： F04D29/544 , F01D5/141 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180087528A1
公开(公告)日：2018-03-29
申请号：US15274352
申请日：2016-09-23
CPC分类号： F04D29/544 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180080465A1
公开(公告)日：2018-03-22
申请号：US15273045
申请日：2016-09-22
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2220/3216 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20180080458A1
公开(公告)日：2018-03-22
申请号：US15271864
申请日：2016-09-21
CPC分类号： F02C3/04 , F01D5/141 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/74 , Y02T50/673
摘要： A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20170370234A1
公开(公告)日：2017-12-28
申请号：US15628764
申请日：2017-06-21
申请人： MTU Aero Engines AG
CPC分类号： F01D5/30 , F01D5/145 , F01D9/041 , F05D2220/323 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2250/711 , Y02T50/673
摘要： The invention relates to a blade or vane, particularly of a turbine stage of a gas turbine, in particular of an aircraft gas turbine, having a blade or vane root and a blade or vane element joined to the blade or vane root, wherein the blade or vane element has a pressure side and a suction side, and wherein the blade or vane root has at least one raised region on its radial outer side facing the blade or vane element. It is proposed according to the invention that the blade or vane has a first raised region on the pressure side and a second raised region on the suction side, wherein the highest point of the first raised region is disposed essentially directly adjacent to the pressure side, and the highest point of the second raised region is disposed essentially directly adjacent to the suction side.
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公开(公告)号：US20170211400A1
公开(公告)日：2017-07-27
申请号：US15410540
申请日：2017-01-19
发明人： Frédéric Vallino
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/16 , F01D25/02 , F05D2220/323 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2300/501 , F05D2300/505 , Y02T50/673
摘要： Stator vane for a turbine engine and including at least one portion made from material suitable for superelasticity. The portion made from material suitable for superelasticity is arranged so as to start to resonate at a predetermined speed of the turbine engine, in particular during a speed of the turbine engine typical of the cruising phase of the aircraft.
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