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公开(公告)号：US10422236B2
公开(公告)日：2019-09-24
申请号：US15667771
申请日：2017-08-03
发明人： William Scott Zemitis , Martin Jasper , Brad Van Tassel , John Wesley Harris, Jr. , Thomas James Brunt
摘要： A turbine nozzle segment includes a radially-inner endwall, a radially-outer endwall, and a pair of airfoil-shaped vanes extending between the radially-inner endwall and the radially-outer endwall. The back face of the radially-inner endwall and/or the back face of the radially-outer endwall has a pocket formed therein in an area between the pressure sidewall of the first vane and the suction sidewall of the second vane to enhance stiffness distribution between the second vane and the radially-inner endwall and/or radially-outer endwall.
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公开(公告)号：US20180023398A1
公开(公告)日：2018-01-25
申请号：US15217033
申请日：2016-07-22
发明人： Jeffrey Clarence Jones , Thomas James Brunt , Jason Anton Byers , Adam John Fredmonski , Hua Zhang
CPC分类号： F01D5/145 , F01D5/186 , F01D5/188 , F05D2220/30 , F05D2240/303 , F05D2240/304 , F05D2250/61 , F05D2250/711 , F05D2250/712 , F05D2260/201 , Y02T50/673 , Y02T50/676
摘要： A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The airfoil body has an inner surface facing the radially extending chamber and an outer surface, a first corrugated surface on a portion of the outer surface, and a second corrugated surface on the inner surface paralleling the first corrugated surface. The corrugated surface on the outer surface of the airfoil provides wake mixing. The blade may also include an integrally formed impingement cooling structure having a third corrugated surface parallel to the second corrugated surface, which is made possible through additive manufacturing. The impingement cooling structure so formed provides improved cooling of the blade.
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3.发明申请公开(公告)号：US20170175576A1
公开(公告)日：2017-06-22
申请号：US14971724
申请日：2015-12-16
发明人： Marc Lionel Benjamin , Gregory Thomas Foster , Benjamin Paul Lacy , Thomas James Brunt , San Jason Nguyen
CPC分类号： F01D25/12 , F01D9/04 , F01D11/12 , F01D11/24 , F01D25/14 , F01D25/246 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/12 , F05D2230/237 , F05D2240/11 , F05D2240/35 , F05D2250/14 , F05D2260/204 , Y02T50/676
摘要： A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have portions with free ends having a width greater than an adjacent portion coupled to the free end.
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公开(公告)号：US20170175574A1
公开(公告)日：2017-06-22
申请号：US14971585
申请日：2015-12-16
CPC分类号： F01D25/12 , F01D5/02 , F01D9/02 , F01D9/04 , F01D11/08 , F01D25/246 , F02C3/04 , F02C7/16 , F04D29/321 , F05D2220/32 , F05D2240/11 , F05D2240/35 , F05D2250/75 , F05D2260/204 , Y02T50/676
摘要： A shroud segment for use in gas turbines, includes a body, leading edge, trailing edge, a first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side of the lateral sides interface with a cavity having a cooling fluid. A second lateral side interfaces with a hot gas flow path. A first channel disposed within the body includes a first and second end portion. A second channel is disposed within the body includes a third and fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The first and fourth end portion have hook-shaped portions with free ends having a width greater than an adjacent portion coupled to the free end.
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公开(公告)号：US10975724B2
公开(公告)日：2021-04-13
申请号：US16175413
申请日：2018-10-30
IPC分类号： F01D25/14
摘要： A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.
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公开(公告)号：US10436037B2
公开(公告)日：2019-10-08
申请号：US15217033
申请日：2016-07-22
发明人： Jeffrey Clarence Jones , Thomas James Brunt , Jason Anton Byers , Adam John Fredmonski , Hua Zhang
摘要： A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The airfoil body has an inner surface facing the radially extending chamber and an outer surface, a first corrugated surface on a portion of the outer surface, and a second corrugated surface on the inner surface paralleling the first corrugated surface. The corrugated surface on the outer surface of the airfoil provides wake mixing. The blade may also include an integrally formed impingement cooling structure having a third corrugated surface parallel to the second corrugated surface, which is made possible through additive manufacturing. The impingement cooling structure so formed provides improved cooling of the blade.
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公开(公告)号：US20190040755A1
公开(公告)日：2019-02-07
申请号：US15667771
申请日：2017-08-03
发明人： William Scott ZEMITIS , Martin JASPER , Brad VAN TASSEL , John Wesley Harris, JR. , Thomas James Brunt
IPC分类号： F01D9/04
CPC分类号： F01D9/047 , F01D9/041 , F01D9/065 , F01D25/246 , F05D2220/32 , F05D2240/128 , F05D2260/941
摘要： A turbine nozzle segment includes a radially-inner endwall, a radially-outer endwall, and a pair of airfoil-shaped vanes extending between the radially-inner endwall and the radially-outer endwall. The back face of the radially-inner endwall and/or the back face of the radially-outer endwall has a pocket formed therein in an area between the pressure sidewall of the first vane and the suction sidewall of the second vane to enhance stiffness distribution between the second vane and the radially-inner endwall and/or radially-outer endwall.
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