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Gas turbine engine air intake in a nacelle

An engine nacelle and gas turbine technology, which is applied to the combustion of the air intake of the power plant, the air intake of the turbine/propulsion device, the gas turbine device, etc. It can solve the problems of component size change, unfavorable weight and size, and achieve weight reduction. , the effect of maintaining aerodynamic performance

Active Publication Date: 2012-07-11
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] A solution could be to strengthen the first compressor stage, however, this strengthening would cause some component dimensional changes, which would be somewhat detrimental to weight and size as these components would need to be able to withstand a direct impact

Method used

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  • Gas turbine engine air intake in a nacelle
  • Gas turbine engine air intake in a nacelle
  • Gas turbine engine air intake in a nacelle

Examples

Experimental program
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Embodiment Construction

[0043] First refer to figure 1 , which shows the main structural components of the unducted turbine engine 10 . From upstream to downstream, along the gas flow direction in the turbine engine, the engine includes a compressor 12, an annular combustor 14, a high pressure turbine 16 (only the turbine casing is shown). Downstream of the high-pressure turbine 16 are two low-pressure turbines (not shown), which are counter-rotating, ie they rotate about the longitudinal axis A of the engine in opposite directions.

[0044] These downstream turbines each rotate because each turbine has a set of outer fan blades 22, 24 extending radially outside the turbine engine nacelle 26, which is generally cylindrical and extends along axis A from The intake port extends around the compressor 12, combustor 14 and turbine.

[0045]The air flow 28 entering the engine is compressed, then mixed with fuel and combusted in the combustion chamber 14, the combustion gases then flow through the turbine...

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PUM

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Abstract

The present invention relates to an assembly comprising a gas turbine engine (10) and a nacelle (26) in which the engine is housed, the nacelle including an air intake fairing (26a) that forms an air inlet and includes: a member for deflecting (40) foreign objects, which, together with said fairing, forms an air intake duct (41); and, downstream from the deflecting member, a secondary deflecting channel (43); and a main (42) channel for supplying air to the engine. Said air intake duct (41) is designed to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel (43). The secondary deflecting channel (43) is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening (43a) leading into the outer wall of the nacelle (26).

Description

technical field [0001] The present invention relates to the field of aero turbine engines, in particular to the air intake of a turbine engine, the latter comprising the engine itself and the nacelle in which it is installed. Background technique [0002] A turbine engine generally includes a gas generator consisting of one or more sets of rotors rotating about a common axis. Each set of rotors usually consists of a shaft or drum-connected compressor and turbine, with one positioned upstream and the other downstream of the combustion chamber, depending on the direction of gas flow through the engine. Connected to the gas generator is the fan or one or more sets of fan blades that it drives. [0003] While the fan rotor or set of fan blades is located at the front of the engine, the inlet to the generator is located downstream of the rotor. Foreign objects (such as birds, hailstones, water and stones) that are easily sucked into the generator will be at least partially slow...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/05F02C7/052F02K3/062F02K3/072F02C7/20
CPCB64D33/02F05D2250/292B64D2033/0293Y02T50/66F02C7/05Y02T50/675F05B2250/70F05B2250/292F02C7/052Y02T50/671F02K3/062F02K3/072F05D2250/70B64D2033/022F05D2260/607B64D2027/005F05B2260/63F02C7/20Y02T50/60
Inventor 飞利浦·杰拉德·查纳兹格坦·吉恩·马鲍克兹飞利浦·吉勒斯·米诺托马斯·阿兰·克里斯蒂安·文森特迪迪尔·吉恩-路易斯·伊冯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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