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公开(公告)号：US10393147B2
公开(公告)日：2019-08-27
申请号：US14807046
申请日：2015-07-23
IPC分类号： F04D29/58 , F28F9/007 , F01D25/28 , B64D29/00 , F02C7/04 , F02C7/32 , F04D29/60 , B64D33/02 , F02K3/06 , F02C7/14 , F04D19/00 , F04D29/02 , F04D29/40 , F04D29/66 , B64D33/08
摘要： A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and forward and aft projections, which are radially spaced from the first surface and located between the peripheral wall and the first surface, and a mounting bracket to mount the surface cooler to the fan casing and a method of mounting a surface cooler to a fan casing of a turbine engine.
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公开(公告)号：US10392950B2
公开(公告)日：2019-08-27
申请号：US14706003
申请日：2015-05-07
摘要： A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.
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公开(公告)号：US10378379B2
公开(公告)日：2019-08-13
申请号：US14836985
申请日：2015-08-27
摘要： A spoolie manifold including two or more spaced apart caps including outlets and one pair of caps connected together in flow communication by a jumper tube assembly. Jumper tube assembly including a jumper tube having first and second spoolies attached to opposite ends of the jumper tube. Ends may be welded into counterbores of the spoolies having spherical spoolie ends press-fitted into first and second sleeves in bores in pair of the caps and sleeves retained in bores with retainer clips. A duct connected in flow communication to an inlet of one of the caps. Spoolie manifold may include three spaced apart caps including a distributor cap between two port caps connected in flow communication to distributor cap by jumper tube assembly. Cap outlets may be feed strut ports in casing of turbine frame including hub spaced inwardly from casing and having spaced apart hollow struts with strut ports.
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公开(公告)号：US10359035B2
公开(公告)日：2019-07-23
申请号：US14514440
申请日：2014-10-15
IPC分类号： G05D23/00 , F04B43/04 , F04F7/00 , F28F13/12 , H01L23/467
摘要： An air agitator assembly for use with a heat-emitting object, where the air agitator assembly includes a perforated flexible plate confronting and spaced from a portion of the heat-emitting object to define an air space there between and at least one piezoelectric structure located on the perforated flexible plate and operably coupled to a power source.
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公开(公告)号：US10344621B2
公开(公告)日：2019-07-09
申请号：US14395938
申请日：2013-04-26
摘要： A system for use in limiting axial movement between a hanger and a fairing assembly within a turbine assembly is provided. The hanger includes an inner radial hanger bend portion that defines a hook channel therein. The fairing assembly includes an outer surface, a hook member extending from the outer surface to mate with the hook channel, and a circumferential groove defined in the outer surface such that at least a portion of the hanger bend portion is positioned between the circumferential groove and the hook member. The system includes a retention member sized for insertion into the circumferential groove, wherein the retention member is configured to extend from the circumferential groove and press against the hanger bend portion to facilitate maintaining the hook member within the hook channel.
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公开(公告)号：US10344602B2
公开(公告)日：2019-07-09
申请号：US15131292
申请日：2016-04-18
发明人： Harjit Hura , Paul Hadley Vitt , Brian David Keith , Jonathan Ong
摘要： A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.
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公开(公告)号：US10323571B2
公开(公告)日：2019-06-18
申请号：US14971354
申请日：2015-12-16
发明人： Sesha Subramanian , Bhaskar Nanda Mondal , Sushilkumar Gulabrao Shevakari , Mayank Krisna Amble
摘要： A method of heating a hollow structure and a heating system are provided. The system includes a plurality of hollow structures spaced circumferentially about an annular flow path. The hollow structures include a heating fluid inlet port, a first plurality of film heating apertures, and a second plurality of film heating apertures. The hollow structures also include a first internal passage extending between the heating fluid inlet port and the first plurality of film heating apertures. The first internal passage includes an impingement leg configured to channel a first flow of heating fluid to a leading edge of the hollow structure. A second internal passage extends between the heating fluid inlet port and the second plurality of film heating apertures through a path along an inner surface of the hollow structure before being channeled to the second plurality of film heating apertures.
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公开(公告)号：US10309244B2
公开(公告)日：2019-06-04
申请号：US15102370
申请日：2014-12-04
摘要： A shroud and shroud hanger are provided wherein at least the shroud is formed of ceramic matrix composite material. The shroud and hanger extend in a circumferential direction. A generally C-shaped clip extends radially to retain the hanger and shroud together.
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公开(公告)号：US10302019B2
公开(公告)日：2019-05-28
申请号：US15059716
申请日：2016-03-03
发明人： Michael Anthony Thomas, Jr. , Curtis William Moeckel , David William Fasig , Carlos Ivan Flores
摘要： Gas turbine engine compressor bleed assembly includes annular bleed plenum between annular outer and inner casings circumscribing compressor flowpath of compressor, upstream and downstream bleed ports disposed through inner casing and between compressor flowpath and plenum at upstream and downstream stages. Bleed path extends from downstream bleed port through bleed plenum and out bleed outlet disposed through outer casing. Autonomously actuated valve such as poppet valve disposed in bleed path or downstream bleed port. Autonomously actuated or poppet valve may be set to open at take-off and/or climb. Bleed outlet may be customer and domestic or engine bleed outlet disposed through outer casing and in fluid bleed air communication with bleed plenum. Another assembly may include annular forward and aft bleed outlets connected to plenums. Bleed path extends from downstream bleed port through plenums and out forward bleed outlet.
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公开(公告)号：US10281153B2
公开(公告)日：2019-05-07
申请号：US15053460
申请日：2016-02-25
摘要： A combustor assembly includes a first combustion chamber member and a second combustion chamber member. The first and second combustion chamber members are each formed of a CMC material and include adjacently positioned coupling flanges. A mounting assembly includes a pair of mounting flanges positioned on opposite sides of the coupling flanges of first and second combustion chamber members. An attachment member of the mounting assembly clamps the pair of mounting flanges together to mount the first and second combustion chamber members.
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