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A wave jet method for blade trailing edge

A trailing edge and waveform technology, which is applied to the supporting elements of the blades, the components of the pumping device for elastic fluids, the non-variable-capacity pumps, etc. Evenly distributed, reducing the effect of turbine noise

Inactive Publication Date: 2016-03-30
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
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Problems solved by technology

However, since the blades are usually thin, if the solid geometry uses a lobe trailing edge, it will inevitably lead to insufficient structural strength of the blade

Method used

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  • A wave jet method for blade trailing edge
  • A wave jet method for blade trailing edge
  • A wave jet method for blade trailing edge

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Embodiment Construction

[0027] In order to better illustrate the purpose and advantages of the present invention, the content of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0028] In this example, an axial-flow turbine blade profile is redesigned according to the method described in the content of the invention, and its effect is verified by numerical methods. The relevant pneumatic parameters of this embodiment are as follows: the total inlet pressure is 111325Pa, and the outlet static pressure is 90000Pa. The design requires that the total pressure loss cannot be lower than 90%, so the preliminary design requires the formation of 5 waveforms, that is, the number of cycles is 5 cycles, that is, at least 5 groups of spoilers are required, and each group has 10 spoiler setting points.

[0029] Step 1. According to a certain original airfoil data and conventional methods, the turbine airfoil shape is given, such as figure 1 sho...

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Abstract

The invention relates to a wavelike jet method for blade trailing edges, which belongs to the technical fields of mechanical devices and transportation. Starting with a pneumatic means, identical rectangular slots are arranged at all the positions along the spanwise direction of a blade, so that jet slots are formed to realize the mechanism of the effect of a physical lobe structure; by creating a model and carrying out numerical calculation to check the model, a trailing edge jet scheme is finalized, spoilers are added, moreover, the opening degree (i.e., the superposing area between the spoilers and the slots) of each spoiler is controlled, and thereby the actual blade is worked out. The disturbance of designed wavelike velocity distribution can achieve the effects of reducing the noise of a fan, a compressor and a turbine and uniformly distributing the inlet flow temperature of downstream turbine blades. The design method is simple, flexible, practical and particularly suitable for the field of aeronautic / ground gas turbines.

Description

technical field [0001] The invention relates to a wave jet flow method for the trailing edge of a blade, and belongs to the technical field of mechanical devices and transportation. Background technique [0002] In response to the development needs of national defense and economic construction, higher requirements are put forward for the performance of aviation / ground gas turbines, including reducing fan / compressor noise and increasing turbine inlet temperature. In order to achieve this requirement, the researchers proposed the method of slotting the jet stream at the trailing edge, and it has been successful. However, after the trailing edge jet, the unevenness of the airflow at the blade outlet is still high, which weakens its noise reduction and cooling effects. [0003] In this regard, the lobe nozzle technology of aviation gas turbines provides a reference for further reducing the unevenness of blade outlet airflow. The lobe nozzle was proposed in the mid-1970s. This ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/26F04D29/66F01D5/14
Inventor 季路成郭鹏马伟涛
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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