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公开(公告)号：CA2582032A1
公开(公告)日：2007-09-24
申请号：CA2582032
申请日：2007-03-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： ABDEL-MESSEH WILLIAM , CUNHA FRANK J
Abstract: A passageway is provided through which a cooling fluid flows in a first direction. The passageway has a plurality of trip strips positioned within the passageway. Adjacent one of the trip strips are oriented to converge towards each other at a first end to form an apex portion and to form a region in which turbulence is created. The apex portion is oriented at an angle with respect to the first direction.
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公开(公告)号：DE602005000449D1
公开(公告)日：2007-03-08
申请号：DE602005000449
申请日：2005-03-16
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , SANTELER KEITH , GAYMAN SCOTT W , COUCH ERIC
Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).
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公开(公告)号：SG121991A1
公开(公告)日：2006-05-26
申请号：SG200506678
申请日：2005-10-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , ALBERT JASON E , PIETRASZKIEWICZ EDWARD F
Abstract: A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which, together with an impingement rib (35), defines a fillet cavity (24) therebetween, and cooling air is provided to flow through impingement holes (26) in the impingement rib (3 5) and impinge on the rear surface (27) of the fillet (18). The impingement holes (26) are elongated in cross sectional shape with their elongations being oriented in a direction generally transverse to a radial direction.
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公开(公告)号：SG121987A1
公开(公告)日：2006-05-26
申请号：SG200506651
申请日：2005-10-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , ALBERT JASON E
Abstract: A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which partially defines a fillet cavity (24) therebehind, and cooling air is provided to the fillet cavity (24) and is then routed to the outer surface by way film cooling holes (41). Various design features are provided to enhance the effectiveness of the cooling air being provided to both the fillet cavity (24) and other cavities within the blade.
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公开(公告)号：SG116534A1
公开(公告)日：2005-11-28
申请号：SG200401642
申请日：2004-03-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , DAHMER MATTHEW T
Abstract: A turbine element airfoil (22) has a cooling passageway network with a slot extending from a trailing passageway toward the trailing edge (32). A number of discrete posts arranged in rows (130-146) span the slot between pressure and suction sidewall portions.
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Patent Agency Ranking
公开(公告)号：EP3074618A4
公开(公告)日：2016-12-07
申请号：EP14864601
申请日：2014-11-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , KOSTKA JR STANISLAV
CPC classification number: F23R3/002 , F01D5/188 , F01D9/023 , F01D25/12 , F02C7/18 , F02C7/24 , F05D2250/21 , F05D2250/23 , F05D2250/232 , F05D2250/24 , F05D2250/241 , F05D2250/324 , F05D2250/712 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F23R3/005 , F23R2900/03042
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公开(公告)号：EP2999927A4
公开(公告)日：2016-05-18
申请号：EP14836500
申请日：2014-05-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , KOSTKA JR STANISLAV
IPC: F23R3/42
CPC classification number: F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors which extend from a cold side thereof. At least one of the multiple of heat transfer augmentors includes a first heat transfer augmentation feature with a second heat transfer augmentation feature stacked thereon.
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公开(公告)号：EP2900977A4
公开(公告)日：2016-04-06
申请号：EP13842463
申请日：2013-09-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , ERBAS-SEN NURHAK
Abstract: A swirler assembly for a gas turbine engine includes an outer annular injector which at least partially surrounds an inner injector. In sonic embodiments, a combustor section for a gas turbine engine comprises an inner injector which defines an axis, an outer annular injector which surrounds said inner injector, and a combustor vane along said axis.
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公开(公告)号：EP3099976A4
公开(公告)日：2017-03-01
申请号：EP15742909
申请日：2015-01-09
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , SNYDER TIMOTHY S
CPC classification number: F23R3/06 , F02C3/14 , F05D2210/33 , F05D2220/32 , F05D2240/35 , F23M5/085 , F23R3/005 , F23R3/007 , F23R3/14 , F23R3/58 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
Abstract: A heat resistant panel has a bulkhead and a swirler adjacent a combustion chamber. The heat resistant panel comprises an inner panel for facing the combustion chamber and defining a first exit port at an upstream end thereof configured to direct cooling air into the combustor chamber in a first direction adjacent the bulkhead. A second exit port at a downstream end thereof is configured to direct cooling air into the combustor chamber in a second direction with an axial direction defined between the upstream and downstream ends. The first and second directions have opposed axial components. A heat resistant structure and a combustor are also disclosed.
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公开(公告)号：EP3071816A4
公开(公告)日：2017-01-18
申请号：EP14863469
申请日：2014-11-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： CUNHA FRANK J , KOSTKA JR STANISLAV
CPC classification number: F23R3/002 , F05D2240/15 , F05D2260/201 , F23R3/005 , F23R3/06 , F23R2900/03044
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