Hybrid nozzle guide vane made of ceramic matrix composite materials

A technology for turbine guides and composite materials, which is applied in the direction of machines/engines, stators, engine components, etc., can solve problems such as complex flow paths, which are difficult to manufacture, achieve high combustion temperatures, reduce weight, simplify cooling flow paths and The effect of additional structure

Active Publication Date: 2013-04-24
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is generally difficult to manufacture such complex flow channels in CMC components

Method used

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  • Hybrid nozzle guide vane made of ceramic matrix composite materials
  • Hybrid nozzle guide vane made of ceramic matrix composite materials
  • Hybrid nozzle guide vane made of ceramic matrix composite materials

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Embodiment Construction

[0037] See Figure 1-Figure 4 , the present invention is a hybrid ceramic matrix composite material turbine guide blade (1), which includes an airfoil part (2) and a core part (5), and the core part (5) is installed inside the airfoil part (2) . The airfoil part (2) is composed of fiber-reinforced ceramic matrix composite material CMC, and the shape of the outer surface (3) of the airfoil part is a cubic spline surface, which determines the aerodynamic shape of the blade, and the shape of the inner surface (4) of the airfoil part Also a cubic spline surface, defining the interior area. The outer surface of the airfoil part (2) is attached with a thermal barrier coating TBC - mullite (2Al 2 o 3 -3SiO 2 ). The shape of the core part (5) corresponds to the inner surface of the airfoil part (2), and the core part (5) is installed inside the airfoil part (2). The inner core part (5) is made of metal material, and a plurality of cooling flow channels (6) are arranged on it, an...

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Abstract

A hybrid nozzle guide vane made of ceramic matrix composite materials comprises a vane-shaped part (2) and a core part (5), the core part (5) is mounted inside the vane-shaped part (2) which is made of fiber reinforced ceramic matrix composite materials, an outer surface (3) of the vane-shaped part is a cubic spline curved surface in shape so as to determine aerodynamic shape of the vane, and an inner surface (4) of the vane-shaped part is also a cubic spline curved surface in shape so that an internal area is determined. The core part (5) is made of metal materials totally different from those of the vane-shaped part (2), the exterior shape of the core part (5) is corresponding to the interior shape of the vane-shaped part (2), a plurality of cooling flow channels (6) are arranged on the core part, heat on a vane body (1) is dissipated by feeding cooling air flow (7), and the cooling air flow (7) flows through the cooling flow channels (6) to flow out of a vane trailing edge (11) finally. Compared with a high-temperature alloy vane, the vane has the advantages that available working temperature is increased, structural weight is reduced, working life is prolonged, and the vane has good application prospect.

Description

technical field [0001] The invention relates to a hybrid ceramic-matrix composite material turbine guide blade, in particular to an internally cooled hybrid CMC (fiber-reinforced ceramic-matrix composite material) blade, which belongs to the technical field of aviation gas turbine engines and ground heavy-duty gas turbines. Background technique [0002] The core of a gas turbine engine consists of a compressor, a combustor, and a turbine. Many combustor and turbine components are directly exposed to the high temperature gas, such as the combustor, the gas flow passage between the combustor and the turbine, the turbine stator blades, the turbine rotor blades and the annular casing section containing them. [0003] We know that as the temperature of the gas increases, the thrust and efficiency of the engine will increase. Gas temperatures in modern high-efficiency gas turbine engines exceed 1600°C, which is beyond the safe operating temperature of materials of construction in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02
Inventor 石多奇牛宏伟
Owner BEIHANG UNIV
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