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Method for controlling radial clearance leakage loss of turbomachine

A technology of radial clearance and impeller machinery, applied in the direction of leakage prevention, mechanical equipment, engine components, etc., can solve the problems of increased total weight of impeller machinery, decreased aerodynamic performance of blade shape, limited effect, etc., and reduces production and use costs , the effect of suppressing the formation of leakage flow and the generation of leakage vortex

Active Publication Date: 2013-11-06
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These methods can reduce the loss caused by the gap to a certain extent and improve the flow inside the turbine channel, but their effect is limited
Moreover, on the one hand, the presence of the shroud will change the local shape of the blade tip, which may lead to a decrease in the aerodynamic performance of the blade; on the other hand, the weight of the rotating blade tip will also increase due to the presence of the shroud. , bringing serious structural strength problems, and at the same time increasing the total weight of the entire turbomachinery, these are what the designers of aero-engines do not want to see
In the compressor, due to the small thickness of the tip of the blade, the above-mentioned technology used in the turbine is difficult to realize, and there is no universally applicable method for controlling the leakage loss of the clearance

Method used

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  • Method for controlling radial clearance leakage loss of turbomachine
  • Method for controlling radial clearance leakage loss of turbomachine
  • Method for controlling radial clearance leakage loss of turbomachine

Examples

Experimental program
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Effect test

Embodiment 1

[0024] Embodiment 1: Retrofitting the flow channel end wall 1 near the front edge of the rotor. Since the intensity of the turbine leakage flow belongs to the middle level, the structure of the leakage vortex 4 also belongs to the middle level of complexity. After preliminary numerical simulation and experiment, a row of spoilers 6 is arranged on the upstream of the rotating blade 2, the number of which is the same as that of the rotating blade 2. When the quantity is the same, better results can be obtained, and the loss of leakage flow is controlled within a smaller range. Spoilers 6 are placed axially at a position of 5.0% of the axial chord length upstream of the rotating blade 2, and are distributed at equal intervals in the circumferential direction. The spoiler 6 is an isosceles trapezoid, and its structure and installation schematic diagram are shown in Figure 3-5 . The lengths of the upper and lower ends of the spoiler 6 are 5mm and 4mm respectively, which are 5.0%...

Embodiment 2

[0025] Embodiment 2: For the turbine of Embodiment 1, in order to expand the action area and scale coverage of the vortex 5 and further improve its suppression of the leakage vortex 4, the following methods can be adopted to obtain a better control effect. The flow channel end wall 1 near the leading edge of the rotor is modified, and two rows of spoilers 6 are axially arranged upstream of the rotating blade 2 . Both rows of spoilers 6 are isosceles trapezoidal, and its structure and installation schematic diagram are shown in Figure 6 and Figure 7 . The first row of spoilers 6 is placed axially at a position of 6.0% of the chord length upstream of the rotating blade 2 , and the second row of spoiler 6 is placed axially at a position of 3.0% of the chord length of the upstream of the rotating blade 2 . All spoilers 6 form an included angle of 10° with the incoming flow direction. In order to reduce the flow loss caused by the spoiler 6 itself, the front and trailing edges...

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Abstract

The invention relates to a method for controlling radial clearance leakage loss of a turbomachine. The invention remodels the end wall near the radial clearance of the turbomachine, thereby changing the flow behavior near the clearance and achieving the goal of reducing flow loss. The remodeling method is mainly realized by arranging a triangular or rectangular or trapezoidal spoiler on the end wall, wherein the spoiler can be welded on the end wall or integrated with the end wall, the height of the spoiler is 2-15% of that of the rotating blade, the axial length of the spoiler is 5-30% of axial chord length of the rotating blade, and the placement direction of the spoiler and the air flow form a certain included angle, thereby generating vortexes which are reverse to the leakage vortexes. The invention effectively controls the flow loss caused by leakage flow and obviously enhances the efficiency of the turbomachine.

Description

technical field [0001] The invention relates to a method for controlling the radial clearance leakage loss of a turbomachinery, which is mainly used for controlling the radial clearance leakage flow loss in a compressor and a turbine in an aeroengine or a gas turbine. Background technique [0002] Compressor and turbine components are important components of power machinery such as aero-engines and ground gas turbines. The efficiency of the entire power machinery is largely determined by the efficiency of the compressor and turbine components, which requires continuous improvement of the efficiency of the compressor and turbine components . [0003] Most of the compressors and turbines used in current aero-engines, ground gas turbines and other power machinery are blade-type. The compressor works on the fluid through the rotating and stationary blade rows, and converts the mechanical energy input from the rotating shaft into the mechanical energy and internal energy of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/08
Inventor 张伟昊邹正平叶建綦蕾刘火星方祥军
Owner BEIHANG UNIV
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