-
公开(公告)号：EP4047273A1
公开(公告)日：2022-08-24
申请号：EP22154371.3
申请日：2022-01-31
发明人： DUDEBOUT, Rodolphe , OZOGUL, Hamdullah , VERMA, Atul , KUJALA, Amy , WEDIG, Michael , MEYER, Ryan , CULBERTSON, Bradley
摘要： A combustor (200) for a gas turbine engine includes an outer liner (202) having a first end interconnected to an opposite second end by an outer liner wall (214) composed of a plurality of outer segments. The inner liner (204) has a first inner end interconnected to an opposite second inner end by an inner liner wall (304) composed of a plurality of inner segments. The outer liner wall (214) and the inner liner wall define a combustion chamber (206), and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments include a first segment (218), a second segment (220) that extends at a second angle relative to the first segment (218), which is less than a third angle defined between the second segment (220) and a third segment (222) and is substantially the same as a fourth angle defined between the third segment (222) and a fourth segment (224).
-
公开(公告)号：EP1671065B1
公开(公告)日：2011-10-05
申请号：EP04794460.8
申请日：2004-10-07
发明人： DUDEBOUT, Rodolphe , REYES, Victor, M. , SCAINI, Mario , DERUDDER, Roger, J. , ZUPANC, Frank, J. , EDMONDS, David, H.
CPC分类号： F23R3/38 , F05B2220/50 , F23R3/52 , F23R3/54
摘要： An auxiliary power unit (APU) includes a rotary fuel slinger, and a singlespool, two-stage turbine. The rotary fuel slinger receives a rotational drive force from the turbine, and a supply of fuel from a fuel source. The rotary fuel slinger injects the fuel into a combustor as a continuous 'fuel sheet.' As a result, fuel mixing and atomization inside the combustor is improved, which reduces emissions and pattern factor, which in turn increases turbine life.
-
公开(公告)号：EP4446565A1
公开(公告)日：2024-10-16
申请号：EP24160466.9
申请日：2024-02-29
发明人： NASIR, Shakeel , VERMA, Atul , KRISE, Jeffrey , TAPEDERI, Doni , SALAI, Jacob , DUDEBOUT, Rodolphe
摘要： A deswirl system for a gas turbine engine includes a deswirl shroud, and at least one deswirl vane having a leading end and a trailing end. The deswirl system includes a deswirl hub spaced apart from the deswirl shroud by the at least one deswirl vane. The deswirl hub includes a hub body that extends at a first angle and a hub extension that extends beyond the trailing end of the at least one deswirl vane. The hub extension extends from the hub body at a second angle, and the first angle is different than the second angle.
-
4.发明公开
公开(公告)号：EP4191138A1
公开(公告)日：2023-06-07
申请号：EP22207199.5
申请日：2022-11-14
发明人： PETERSON, Duane , KANAKAGIRI, Girish , BASANI, Jaydeep , RUDRAPATNA, Nagaraja , YANKOWITCH, Paul , BOHMAN, Richard R. , DUDEBOUT, Rodolphe , PRASAD, Venkatesha
IPC分类号： F23R3/34
摘要： An injector module (42) includes an injector stem (102) that extends along an injector longitudinal axis (31) between an inlet end (90) and an outlet end (92) of the injector module (42). The injector module (42) also includes a first fuel line (121) of a first fuel circuit (131) at least partly extending through the injector stem (102). The first fuel line (121) has a first outlet (116) disposed at the outlet end (92) of the injector stem (102). The injector module(42) further includes a second fuel line (122) of a second fuel circuit (132) at least partly extending through the injector stem (102). The second fuel line (122) has a second outlet (118) disposed at the outlet end (92) of the injector stem (102). The first outlet ((116) and the second outlet (118) are spaced apart and have different orientations relative to the injector longitudinal axis (31). The first fuel line (121) is thermally coupled to the second fuel line (122).
-
公开(公告)号：EP3660400A1
公开(公告)日：2020-06-03
申请号：EP19211061.7
申请日：2019-11-22
发明人： DUDEBOUT, Rodolphe , RUDRAPATNA, Nagaraja S. , VERMA, Atul , CHOU, David , ZOLLARS, Christopher
摘要： A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
-
公开(公告)号：EP4089265A1
公开(公告)日：2022-11-16
申请号：EP22159609.1
申请日：2022-03-02
摘要： A coating occlusion resistant effusion cooling hole (300) to form a film of a cooling fluid on a surface of a wall (308). The cooling hole extends along a longitudinal axis (LA). The cooling hole includes an inlet section (310) defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section (316) fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section (318) fluidly coupled downstream of the metering section. The outlet section includes an overhang portion (348) , a recessed portion (350,352), a first sidewall (354) and a second sidewall (356). The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.
-
-
公开(公告)号：EP4350218A1
公开(公告)日：2024-04-10
申请号：EP23198091.3
申请日：2023-09-18
发明人： DUDEBOUT, Rodolphe
摘要： A gaseous fuel nozzle (112) includes a main body (302), a plurality of inner air injection passages (304) having inlet (314) and outlet (316) ports, a plurality of outer air injection passages (306) having inlet (318) and outlet (322) ports, and a plurality of gaseous fuel injection passages (308)having inlet (324) and outlet (326) ports. At least the gaseous fuel injection outlet ports (322) are disposed concentrically about an axis of symmetry (310) and between the plurality of inner air injection nozzle outlet ports and the plurality of outer air injection nozzle outlet ports.
-
公开(公告)号：EP3447386B1
公开(公告)日：2020-10-07
申请号：EP18190604.1
申请日：2018-08-24
发明人： DUDEBOUT, Rodolphe , JAMES, Sunil
-
10.发明公开
公开(公告)号：EP3415718A3
公开(公告)日：2019-01-23
申请号：EP18157514.3
申请日：2018-02-20
IPC分类号： F01D5/18
摘要： A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.
-
-
-
-
-
-
-
-
-
搜索结果
12 条记录 (耗时 0.012 秒)
