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Double-row nozzle structure for cold air prerotation

A cold air pre-rotation and nozzle technology, which is applied in the cooling of the engine, the cooling of the turbine/propulsion device, the engine components, etc., can solve the problems of the heat exchange difference at the low radius of the turntable, and achieve the increase of the total area, the total flow rate, The effect of temperature reduction

Pending Publication Date: 2018-06-19
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the constraints of the existing nozzle inlet area and the problem of poor heat transfer at the low radius position of the turntable, the present invention proposes a new row of pre-swirl nozzles at the low radius position of the static disk in the rotating and static disk cavity

Method used

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  • Double-row nozzle structure for cold air prerotation
  • Double-row nozzle structure for cold air prerotation
  • Double-row nozzle structure for cold air prerotation

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Embodiment

[0026] This embodiment is a double-row pre-swirl nozzle used in a pre-swirl system, including a circle of high-radius nozzles 1 at a high-radius position and a circle of low-radius nozzles 2 at a low-radius position. The air flows from the air intake cavity into the rotating disc cavity 4 through two rows of nozzles at high and low radius positions respectively, which can improve the heat exchange effect at the low radius position of the rotating disc 6 .

[0027] The structural parameters of the double-row nozzles in this embodiment: r 1 The radius of rotation of the high radius nozzle, r 2 Rotation radius of low radius nozzle, β 1 Angle between every two high radius nozzles, β 2 Angle between every two low radius nozzles, β 3 The circumferential angle between a high-radius nozzle and a low-radius nozzle, θ pre-swivel angle.

[0028] The high-radius nozzles and low-radius nozzles are evenly distributed along the circumferential direction. The angle θ between the nozzle an...

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Abstract

The invention discloses a double-row nozzle structure for cold air prerotation. A nozzle is mainly composed of two parts, namely a circle of nozzles at the high radius position and a circle of nozzlesat the low radius position. Airflow enters the two rows of nozzles at the high position and the low position from an air intake cavity, and enters a rotor and stator cavity at a certain angle. The double-row nozzle structure for cold air prerotation is widely applied to high-temperature component cooling systems of an aircraft engine and a ground gas turbine, and has the beneficial effects that compared with a common single-row prerotation nozzle, the total air intake area of the nozzles can be enlarged, the angle of lag of airflow in the nozzles is reduced, the flow coefficient of the nozzles is increased, heat exchange of the low radius position of a rotary plate can be improved while the prerotation nozzles obtain a large dimensionless temperature drop, accordingly the temperature gradient of the rotary plate is reduced, and flow adjustability of the cooling system can be achieved.

Description

technical field [0001] The invention relates to the technical field of pre-swirling cooling in air systems of rotating turbomachinery (aeroengines, ground gas turbines, etc.), and relates to a double-row nozzle structure for cold air pre-swirling. Background technique [0002] In recent years, the continuous improvement of aero-engine cycle parameters, especially the increase of gas temperature before the turbine, has caused a sharp increase in the thermal load of the hot-end components such as the turbine disk and turbine blades of the engine, and its service life and reliability of safe operation have been severely restricted . The pre-swirling nozzle is an important component of the pre-swirling system. Its function is to provide cooling gas to cool the turbine disk and turbine blades of the engine, and to provide sealing gas for the sealing of the disk edge, thereby prolonging the service life and reliability of the blades. sex. [0003] After the high-pressure gas is ...

Claims

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Application Information

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IPC IPC(8): F02C7/18F01D25/12
CPCF01D25/12F02C7/18
Inventor 王锁芳胡伟学毛莎莎夏子龙
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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