Turbine blade pressure surface cooling structure
A technology for cooling structure and turbine blades, which is applied in the direction of blade support components, engine components, machines/engines, etc. It can solve the problems of unable to meet the cooling requirements of turbine blades, low efficiency of air film cooling, unfavorable blade cooling, etc., and achieve improved air conditioning Effects of utilization rate, improvement of film cooling efficiency, and reduction of cooling air consumption
Pending Publication Date: 2022-03-01
AECC SHENYANG ENGINE RES INST
View PDF0 Cites 1 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
The composite cooling structure commonly used in third- and fourth-generation machines can no longer meet the cooling requirements of turbine blades when the inlet temperature is above 2000K
[0006] c) Single-layer wall structure, thick wall thickness, large thermal resistance, which is not conducive to blade cooling;
[0007] d) Circular air film holes are generally used, and the air film cooling efficiency is low
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment Construction
[0030] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the present application will be described in detail below in conjunction with...
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
The invention belongs to the field of aero-engine blades, and particularly relates to a turbine blade pressure surface cooling structure. Comprising the steps that a plurality of cooling units are arranged on the blade pressure face, the cooling units are divided into multiple sections through partition ribs, and the cooling units are provided with impact holes and impact cavities communicating with the impact holes; the cross flow area is provided with turbulent flow columns, turbulent flow channels are arranged between the turbulent flow columns, and the turbulent flow channels are communicated with the impact cavity; the outlet section is provided with throttling columns, the throttling columns comprise the first throttling column and the second throttling column, the upstream sections of the two adjacent wall faces of the first throttling column and the second throttling column are in a concentric circle mode, the downstream sections of the two adjacent wall faces of the first throttling column and the second throttling column are in an expansion mode, and an annular throttling channel upstream section is formed between the upstream sections of the two wall faces in the concentric circle mode. An expanded throttling channel downstream section is formed between the two expanded wall surface downstream sections, the throttling channel upstream section and the throttling channel downstream section jointly form a throttling channel, the throttling channel is communicated with the turbulent flow channel, and an air film hole is further formed in the outlet section.
Description
technical field [0001] The application belongs to the field of aeroengine blades, in particular to a cooling structure for the pressure surface of a turbine blade. Background technique [0002] With the development of aviation technology, the performance of aero-engines continues to improve, and the temperature in front of the turbine continues to rise. The temperature in front of the turbine has increased from 1700K to 2000K, which greatly increases the heat load on the turbine blades; at the same time, in order to pursue As engine efficiency increases, the amount of cooling air used by turbine blades continues to decrease. The composite cooling structure commonly used in third- and fourth-generation engines can no longer meet the cooling requirements of turbine blades when the inlet temperature is above 2000K. [0003] At present, most of the composite cooling structures adopt the cooling method of impact convection + air film. The cold air passes through the impact holes...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 王焘李懋源卢元丽
Owner AECC SHENYANG ENGINE RES INST