Cooling device for a turbine of a turbomachine
A technology of a cooling device and a turbine, applied in the field of cooling devices of a turbine, can solve the problems of reducing the cooling of the casing, restricting heat dissipation, and being unfavorable for effective cooling in service life, and achieving the effect of reducing the overall radial size
Active Publication Date: 2019-06-18
SAFRAN AIRCRAFT ENGINES SAS
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Problems solved by technology
[0013] However, it has been noted that the metal plate insulates the area between the metal plate and the wear resistant material and restricts air circulation in this area, thereby limiting heat dissipation, making this area relatively hot, which is not conducive to its use life and more generally prevents effective cooling of the area concerned
This results in reduced case cooling in areas where heat dissipation is restricted, and impacts on turbine efficiency
Method used
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[0054] Figure 1 shows a part of a turbofan engine, in particular a low pressure turbine 1, according to the invention. This consists of a rotor with wheels 2 axially connected to each other by annular flanges 3 , each wheel comprising a disk 4 carrying blades 5 .
[0055] A number of annular rows of stationary blades 6 are mounted by suitable means at their radially outer ends on the casing 7 of the low-pressure turbine 1 between the movable wheels 2 .
[0056] A ring 8 carrying wear resistant material surrounds the outer circumference of the blades 9 of each impeller 2 .
[0057] As previously mentioned, the main air flow F1 from the combustion chamber circulating in the main section 10 significantly heats the casing 7 and the ring 8 .
[0058] To ensure cooling of the housing 7 , the turbofan includes a cooling device 11 not shown in FIG. 1 but visible in FIGS. 2 to 4 .
[0059] This includes air sampling and supply equipment including an air vent provided, for example, in...
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The invention relates to a cooling device (11) for a turbine of a turbomachine extending along an axis, comprising at least one radially inner metal sheet (14) and a radially outer metal sheet (15) that are joined to one another and delimit, between them, cooling air circulation channels (17) extending circumferentially from a connection region (16), each channel (17) comprising at least one air inlet and air ejection orifices (19) that are designed to be oriented toward a region that is to be cooled, characterized in that it comprises means for cooling said metal sheets comprising at least one cooling duct (21) intended for the circulation of cooling air, said duct (21) being located radially outside said metal sheets (14, 15) and close to or in contact with said metal sheets so as to cool said metal sheets using the cooling air circulating in the duct (21), the cooling duct (21) extending axially and being arranged opposite circumferential end regions of the channels (17).
Description
technical field [0001] The invention relates to a cooling arrangement for a turbine of a turbomachine, such as an aircraft turbojet engine, in particular a turbofan engine. Background technique [0002] A turbofan engine generally includes a fan with the following extending downstream from the fan: [0003] - the main section, in which the main flow circulates, which passes in the direction of the main flow circulation through the low-pressure compressor, the high-pressure compressor, the combustion chamber, the high-pressure turbine and the low-pressure turbine, the main section consisting of where the turbine is externally bounded by the turbine housing, [0004] - a sub-section in which a secondary stream different from said main stream circulates, [0005] A low-pressure turbine comprises in particular several successive stages comprising impellers and stationary parts. The impeller has a disk on which the blades are mounted. The ends of the blades are surrounded by ...
Claims
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IPC IPC(8): F01D11/24
CPCF01D11/24F05D2260/201Y02T50/60F05D2220/36F01D25/14
Inventor 巴普蒂斯特·玛丽·奥宾·皮埃尔·茹伊尼古拉斯·孔蒂尼阿诺·杜布利耶文森特·杜波伊斯·多罗吉塞巴斯蒂安·让·劳伦·帕莱斯特尔
Owner SAFRAN AIRCRAFT ENGINES SAS