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Hollow blade

A hollow blade and vane technology, which is applied to the components of pumping devices for elastic fluids, non-variable displacement pumps, machines/engines, etc., can solve the problems of difference in impact resistance and uneven rigidity of blades

Inactive Publication Date: 2013-03-27
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

A U.S. patent US6,979,180 owned by Rolls-Royce discloses a hollow fan blade, which has a titanium alloy structure in the shape of a "valun plate" inside, although as a whole, it has The blades of this structure have good rigidity and anti-bird strike characteristics. However, since the shape of the "Valen board" is composed of multiple trapezoids, and the trapezoidal structure itself has the characteristics of uneven rigidity, it will cause the blades to Technical issues with impact resistance differences

Method used

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Embodiment Construction

[0026] like Figure 1-Figure 2 As shown, among them, figure 2 (a) and (b) represent two different airfoil types, namely symmetrical airfoil type and curved and twisted airfoil type. The fan blade 10 includes a tenon 11 and an airfoil profile 12 . The tenon 11 has a wedge shape or other suitable shape for being installed in a correspondingly shaped tenon groove on the fan disc 13 . The airfoil profile 12 has a pressure side portion 16 and a suction side portion 17 extending from a leading edge 14 to a trailing edge 15, in combination with image 3 , The pressure surface part 16 and the suction surface part 17 are respectively formed by panels 20, 22, and the material of the panels 20, 22 is titanium alloy. Optionally, the panels 20, 22 can also be made of steel, such as stainless steel. In the cavity formed by the pressure surface portion 16 and the suction surface portion 17, there is also a vibration damping portion 18, which is arranged at intervals from the leading edg...

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Abstract

The invention relates to a hollow blade, which comprises a root tenon and a blade profile part, wherein the blade profile part extends to a top end from the root tenon, and is provided with a front edge, a tail edge, and a pressure surface part and a suction surface part extending from the front edge to the tail edge; the pressure surface part and the suction surface part commonly limit a cavity; and a vibration resistance part is connected onto an inner surface of the cavity, and is provided with a plurality of hollow like hexagonal cylinder structures arranged between the front edge and the tail edge at intervals and extending from the root tenon to the top end. The blade with the hollow hexagonal cylinder structures, so that the rigidity in each direction is balanced, and the impact resistance of the blade in each direction is effectively enhanced.

Description

technical field [0001] The invention relates to a hollow blade, in particular to a hollow fan blade used in an aero-engine. Background technique [0002] Aviation turbofan engine includes fan part, compressor part, combustor part, turbine part and exhaust part etc. The fan part includes the fan rotor and casing stator. The fan rotor is composed of fan blades, discs and shafts. There are many types of blade structures, and hollow fan blades are one of the structure types. [0003] The wide-chord hollow blade has the advantages of high efficiency, light weight, strong resistance to foreign object damage, and increased surge margin of the compressor. Moreover, the number of single-stage fan blades can be reduced by adopting this new structure, and the weight of the engine can be further reduced. Many advanced aviation turbofan engines have adopted the structural design of wide-chord hollow fan blades. [0004] In 1968, Rolls-Royce of the United Kingdom began to design and d...

Claims

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Application Information

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IPC IPC(8): F04D29/38
Inventor 喻双喜刘业胜段肖珑
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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