System including counter-rotating propellers driven by an epicyclic train ensuring a balanced couple distribution between the two propellers

一种对转螺旋桨、行星齿轮的技术，应用在螺旋桨、发动机元件、发动机功能等方向，能够解决涡轮机副作用、减速比率螺旋桨系统总质量增加、不利于增加涡轮机声级等问题，达到减小比率减小、小尺寸的效果

Active Publication Date: 2011-11-23
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

In addition, an increase in the reduction ratio inevitably leads to an increase in the total mass of the propeller system, which has a negative effect on the turbine
[0009] Due to the unequal ratio between the torques, one of the two propellers will generate a larger secondary flow slew than the other, causing a residual slew of the output flow, somewhat limiting propulsion efficiency, and not conducive to increasing the sound level of the turbine

Method used

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  • System including counter-rotating propellers driven by an epicyclic train ensuring a balanced couple distribution between the two propellers
  • System including counter-rotating propellers driven by an epicyclic train ensuring a balanced couple distribution between the two propellers
  • System including counter-rotating propellers driven by an epicyclic train ensuring a balanced couple distribution between the two propellers

Examples

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Embodiment Construction

[0033] refer to figure 1 , an "open rotor" type turbine 1 according to a preferred embodiment of the present invention can be seen.

[0034] In the figures, direction A refers to the longitudinal or axial direction, parallel to the longitudinal axis 2 of the turbine. For this part, direction B refers to the radial direction of the turbine. Furthermore, the arrow 4 shows the direction of movement of the aircraft under the impetus of the turbine 1 , wherein this direction of movement is opposite to the general flow direction of the gas in the turbine. The terms "front end", "upstream", "rear end", "downstream" used in the rest of the description should be considered relative to said direction of movement 4 .

[0035] In the front part, the turbine has an air intake 6 which is connected to the rear end via a nacelle 8 . Here, the latter comprehensively includes an outer coating 10 and an inner coating 12 , the two latter being centered on the axis 2 and offset from each other ...

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Abstract

The present invention relates to a system of counter-rotating propellers (30) for an aircraft turbine engine, including: a free power turbine (32) including a first rotor (32a); first and second propellers (7, 9); and a mechanical transmission device (13) including an epicyclic train (15) with a planetary gear (17) driven by the rotor (32a), at least one satellite (21), a satellite carrier (25) driving the first propeller (7) and a gear (31) driving said second propeller (7). According to the invention, the free turbine (32) also includes a second rotor (32b) counter-rotating relative to the first rotor (32a) and rotating the gear (31).

Description

technical field [0001] The present invention generally relates to a contra-rotating propeller system for an aircraft turbine. [0002] The invention also relates to a turbine for an aircraft comprising such a contra-rotating propeller system. [0003] Preferably, the invention is applicable to aircraft turbines, such as jet turbines, turboprops. It has particular application to turbines known as "open rotor" turbines, in which a free power turbine drives two counter-rotating propellers directly or indirectly through a mechanical transmission system forming a reduction gear And includes a planetary gear train. Therefore, in this contra-rotating propeller system, the propeller has no fairings at its outer diameter end. Background technique [0004] In the prior art, turbines with contra-rotating propeller systems are known, wherein the contra-rotating propellers are driven by a mechanical transmission system, customarily in the form of differential reduction gears. This di...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/067F02C7/36F02K3/072
CPCY02T50/671F05B2260/40311F05D2260/40311Y02T50/66F02C7/36F02C3/067B64C11/48F05D2260/96F05B2260/96F02K3/072Y02T50/60
Inventor 沃特·鲍克吉勒斯·阿兰·查瑞尔弗朗索瓦·加莱特
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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