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Assembly for turbomachine blade comprising fastener defining pocket and wedge adapted to be received in pocket simultaneously with root of blade

A technology for turbine blades and blade roots, applied in parts of pumping devices for elastic fluids, supporting elements of blades, aircraft parts, etc., can solve problems that cannot be effectively eliminated

Pending Publication Date: 2022-07-08
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0014] However, such deformable wedges are not effective in eliminating this flutter phenomenon in blades with variable pitch fans and wide chord and / or large size fans where even at low fan speeds There are also particularly strong aerodynamic forces under the

Method used

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  • Assembly for turbomachine blade comprising fastener defining pocket and wedge adapted to be received in pocket simultaneously with root of blade
  • Assembly for turbomachine blade comprising fastener defining pocket and wedge adapted to be received in pocket simultaneously with root of blade
  • Assembly for turbomachine blade comprising fastener defining pocket and wedge adapted to be received in pocket simultaneously with root of blade

Examples

Experimental program
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Embodiment Construction

[0048] exist figure 1 , the engine 1 is shown in what is currently known as a "propeller" configuration (i.e. the fan is placed at the rear of the power generator, the air intake is figure 1 right), "open rotor" type engine.

[0049] The engine comprises a nacelle 2 and an unducted fan 3, the nacelle being intended to be fixed to the fuselage of the aircraft. The fan 3 includes two counter-rotating fan rotors 4 and 5 . In other words, when the engine 1 is running, the rotors 4 and 5 are arranged to rotate in opposite directions relative to the nacelle 2 about the same axis of rotation X, which coincides with the main axis of the engine.

[0050] exist figure 1 In the example shown in the engine 1 is an "open rotor" type engine in a "propeller" configuration with counter-rotating fan rotors. However, the present invention is not limited to this configuration. The invention is also applicable to "open rotor" type engines in a "puller" configuration (ie, the fan is arranged ...

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Abstract

Assembly for a turbomachine blade, the assembly comprising: a fastener (9) defining a pocket (10) for receiving a blade root (11) and comprising two flanks defining between them a passage leading to the pocket (10) and forming a stop preventing the root (11) from exiting the pocket (10) via the passage; and a wedge portion (26a, 26b) adapted to be received in the pocket portion (10) together with the root portion (11), the wedge portion (26a, 26b) having a first support surface (28a, 28b) for bearing on the root portion (11) and a second support surface (30a, 30b) opposite the first support surface (28a, 28b) for bearing against the fastener (9), the support surfaces being fixed relative to each other, the wedge portion (26a, 26b) being adapted to be received in the pocket portion (10) together with the root portion (11), the wedge portion (26a, 26b) being adapted to be received in the pocket portion (10) together with the root portion (11). The root portion (11) has a wedge portion (26a, 26b) and is oriented such that movement of the wedge portion (26a, 26b) in the pocket portion (10) relative to the fastener (9) changes a value of a force exerted by the wedge portion (26a, 26b) on the root portion (11).

Description

technical field [0001] The present invention relates to an assembly for securing blades to parts of an aircraft engine rotor, in particular a rotor of a non-ducted fan (for example an engine of the "open rotor" type with two turning spirals, or with a movable Bladed and fixed-blade Unducted Single Fan (USF) type engines, or turboprops with a single-screw architecture). Background technique [0002] The benefit of a ductless fan engine is that the diameter of the fan is not limited by the presence of a fairing, enabling the design of an engine with a high dilution ratio, thereby reducing fuel consumption. [0003] Therefore, in this type of engine, the blades of the fan can have larger dimensions. [0004] Such ductless fans typically include blade fasteners that define pockets for receiving the roots of the blades. The blade fastener includes two opposing flanks that define a channel between the two opposing flanks to the pocket and form a stop that prevents the root from ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C11/06
CPCB64C11/06B64C11/32F04D29/323F01D5/3007B64D2027/005F05D2260/31F01D7/00F05D2220/36F01D5/3015F01D1/26F01D5/323Y02T50/60F01D5/326
Inventor 薇薇安·米卡尔·考提尔克里斯多夫·保罗·雅克马德文森特·朱登
Owner SAFRAN AIRCRAFT ENGINES SAS