Device for shifting a propeller into reverse, comprising an actuator acting on a crank pin

A technology for propellers and crank pins, which is applied to the arrangement/installation of propellers, power units, engine components, etc., and can solve problems such as broken blades, engine speeding, overspeed, etc.

Active Publication Date: 2013-09-04
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

If this is not the case, if the propeller is always at the zero pitch setting, the opening of the throttle will cause the engine to fly, causing the risk of overspeed and consequently breaking the bla

Method used

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  • Device for shifting a propeller into reverse, comprising an actuator acting on a crank pin
  • Device for shifting a propeller into reverse, comprising an actuator acting on a crank pin
  • Device for shifting a propeller into reverse, comprising an actuator acting on a crank pin

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Embodiment Construction

[0032] refer to figure 1, the figure shows a high-speed propeller turbine engine 1, which includes, on the one hand, a conventional gas generator, which in turn includes a compressor 2, a combustion chamber 3 and a turbine 4, the turbine 4 drives the compressor 2, and the other Aspects include, downstream of the coupling turbine 4, a free turbine 5 driving two sets of coaxial counter-rotating propellers 6 blades. The propeller is arranged outside the gas generator housing 7, and its blades are held by blade roots 8 that can rotate around an axis that is radial to the turbine 1 and passes through the center of the blade roots to form the main axis of the blades. The blade is driven to rotate by the transmission mechanism, which is in the form of a linkage device 9 and acts on a pair of helical gears, one of which is fixed on the blade and surrounds the blade root 8 . As previously stated, these helical gears are sized such that a reduction ratio of 2 is such that, when the ass...

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Abstract

The invention relates to a device for controlling the shifting of a propeller turbine engine into reverse mode, by acting on a shaft (13) for controlling the pitch of the propellers. The device comprises: at least one centrifugal weight (14) arranged to drive the propellers into the flag position thereof under the action of the centrifugal force; and an actuator (9) that can rotate the control shaft (13) in order to shift the pitch of the propellers from a traction mode to a reverse mode, passing through a zero pitch position. The invention is characterised in that the centrifugal weight (14) is in an unstable equilibrium position in relation to the action of the centrifugal force when the control shaft shifts the pitch of the propellers (6) through the zero pitch position. In addition, the invention comprises an actuation means (19) that exerts a torque on the control shaft (13) when the centrifugal weight is in the unstable equilibrium position, so as to prevent it from staying in this position.

Description

technical field [0001] The present invention relates to the field of aeronautical turbine engines, and in particular to the field of turbine engines or high-speed propeller engines with unducted propellers known as "open rotors", and the field of devices for controlling the direction of the blades of such propellers. Background technique [0002] Aviation engine technology is developing very fast, and one of the aspects being studied is to improve the fuel consumption rate of civil aircraft engines, and this aspect currently refers to the development of open rotor engines. This engine, as described in the applicant's company patent application FR2941493, comprises a conventional turbine engine gas generator, one or more of which turbine stages drive an unducted fan extending outside the engine. Considering the desired thrust level and the reduction of blade noise, the engine is usually equipped with two coaxial counter-rotating unducted propellers, that is to say, the two pr...

Claims

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Application Information

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IPC IPC(8): B64C11/34B64C11/32
CPCB64C11/325B64C11/346B64C11/48B64D2027/005Y02T50/60F01D7/00
Inventor 弗朗索瓦·加列特
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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