A turbine guide and its large expansion ratio centripetal turbine
A turbine guide and guide technology, applied in the direction of machine/engine, stator, mechanical equipment, etc., can solve the problems of low power-to-weight ratio and large radial size of the engine, and improve the power-to-weight ratio, reduce the outer diameter, The effect of reducing the weight of the turbine
Active Publication Date: 2022-08-02
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0004] The invention provides a turbine guider and a centripetal turbine with a large expansion ratio using the guider, to solve the technical problem that the current turbine guider has a large radial dimension which results in a low power-to-weight ratio of the engine
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[0037] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways as defined and covered below.
[0038] like figure 1 and figure 2 As shown, the preferred embodiment of the present invention provides a turbine guide, which is applied to a radial turbine with a large expansion ratio, which includes a guide outer ring 1, a guide inner ring 2 and a plurality of guide vanes 3, the The guide outer ring 1 and the guide inner ring 2 are symmetrically arranged around the engine axis, an annular airflow channel is formed between the guide outer ring 1 and the guide inner ring 2, and a plurality of guide vanes 3 are spaced at the same angle in the circumferential direction Evenly arranged in the annular airflow channel. Wherein, the annular airflow channel is generally inverted L-shaped from a side view, that is, after the annular airflow channel extends a...
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The invention discloses a turbine guide and a large expansion ratio centripetal turbine using the same. The guide includes an outer guide ring, an inner guide ring and a plurality of guide vanes. The guide outer ring and the guide inner ring are symmetrical around an engine axis. Arrangement, an annular airflow channel is formed between the outer ring of the guide and the inner ring of the guide. After the annular airflow channel extends for a certain length in the axial direction at the inlet of the centripetal turbine, it is turned 90° to form an airflow channel distributed along the radial direction. The guide vanes are evenly arranged in the annular airflow channel at the same angle in the circumferential direction. The radius ratio is between 1.1 and 1.3. The present invention can effectively reduce the outer diameter of the entire guide by reducing the height of the straight section of the guide inlet and reducing the radius ratio of the guide vane between the inlet and the outlet. This reduces the weight of the turbine and increases the power-to-weight ratio of the engine.
Description
technical field [0001] The present invention relates to the technical field of radial turbine guide design, in particular, to a turbine guide, and also to a large expansion ratio centrifugal turbine using the above-mentioned turbine guide. Background technique [0002] Small gas turbine engines and aviation auxiliary power units generally adopt the core structure layout of centrifugal compressor, annular return combustion chamber and centripetal turbine due to the compact structure. At present, a major development trend of gas turbine engines is to gradually develop towards higher power-to-weight ratio and higher thermodynamic cycle parameters. In order to increase engine output power and reduce engine weight, the temperature before the turbine and the single-stage turbine expansion ratio are constantly increasing. For a single-stage centripetal turbine with an expansion ratio exceeding 4.0, both the turbine guide and the impeller flow channel may be in a supersonic flow sta...
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IPC IPC(8): F01D9/04F01D25/12
CPCF01D9/041F01D9/045F01D25/12
Inventor 欧阳玉清宋友富杨伟平潘尚能杨玲谢昌坦
Owner AECC HUNAN AVIATION POWERPLANT RES INST