Unlock instant, AI-driven research and patent intelligence for your innovation.

A method for controlling blade profile size

A size control and blade technology, which is applied in the direction of core, casting mold, casting mold composition, etc., can solve the problem of not considering the impact of the fatigue performance and weight of the working blade airfoil shape, and achieve the effect of meeting the weight requirements of the blade

Active Publication Date: 2020-12-29
AECC AVIATION POWER CO LTD
View PDF5 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The working blades of the aeroengine turbine are the rotating parts in the engine. They work in a very harsh environment. In order to improve the thrust-to-weight ratio of the engine, the weight of the working blades is required to fluctuate within a certain range; It has a certain fatigue strength. In addition to meeting the weight and fatigue performance, the blade size, especially the blade shape size, must also meet the requirements of the design drawings, and the tolerance requirements for the blade shape of the aeroengine turbine blade are very strict. Therefore, the working blade needs to be at the same time Satisfy the requirements of weight, fatigue performance and airfoil size. In the previous work blade airfoil size design, only the different shrinkage of the blade in the three-dimensional direction and the offset of the subsequent processing for the reduction of the airfoil size were considered. The influence of the blade size design of the working blade on the fatigue performance and weight, while the weight and fatigue performance of the working blade are mainly reflected in the blade shape size

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 more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • A method for controlling blade profile size
  • A method for controlling blade profile size
  • A method for controlling blade profile size

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0044] The airfoil tolerance of the first-stage working blade of a low-pressure turbine is ±0.14mm, four blade sections S1-S4 are selected, S1 is close to the blade tip 1, S4 is close to the joint between the blade body and tenon root 3, H=127.04mm, H1=113.56 mm, H2=96.53mm, H3=64.85mm, H4=9.41mm, when the wax mold is designed, after the blade is placed with a shrinkage rate of 1.8% in the X and Y directions, and a shrinkage rate of 2.25% in the Z direction, the blade body and tenon The maximum leaf shape offset L=0.07mm after the wax model shrinks at the root joint 3, then there is:

[0045]

[0046]

[0047]

[0048]

[0049] The blade profile offset at the blade tip is 0mm.

[0050] After adopting the above optimized design scheme of the wax mold, the dimensional accuracy of the first-stage working blade of the low-pressure turbine of a certain machine is good, and the weight and fatigue performance of the blade meet the requirements of the design drawings.

Embodiment 2

[0052] The airfoil tolerance of the second-stage working blade of a low-pressure turbine is ±0.13mm. Four blade sections S1-S4 are selected. S1 is close to the blade tip 1, S4 is close to the joint between the blade body and the root 3, H=158.6mm, H1=125.23 mm, H2=100.89mm, H3=50.21mm, H4=12.47mm, when the wax mold is designed, the blade is placed with a shrinkage rate of 1.9% in the X and Y directions, and a shrinkage rate of 2.3% in the Z direction. The maximum leaf shape offset L=0.13mm after the wax model shrinks at the root joint 3, then there is:

[0053]

[0054]

[0055]

[0056]

[0057] The blade profile offset at the blade tip is 0mm.

[0058] After adopting the above optimized design scheme of the wax mold, the dimensional accuracy of the first-stage working blade of the low-pressure turbine of a certain machine is good, and the weight and fatigue performance of the blade meet the requirements of the design drawings.

Embodiment 3

[0060]The airfoil tolerance of the four-stage working blade of a low-pressure turbine is ±0.13mm, four blade sections S1-S4 are selected, S1 is close to the blade tip 1, S4 is close to the joint between the blade body and the tenon root 3, H=207.96mm, H1=170.24 mm, H2=130.82mm, H3=64.57mm, H4=15.18mm, when the wax mold is designed, the blade is placed with a shrinkage rate of 2.0% in the X and Y directions, and a shrinkage rate of 2.4% in the Z direction. The maximum leaf shape offset L=0.13mm after the wax model shrinks at the root joint 3, then there is:

[0061]

[0062]

[0063]

[0064]

[0065] The blade profile offset at the blade tip is 0mm.

[0066] After adopting the above optimized design scheme of the wax mold, the dimensional accuracy of the four-stage working blade of a low-pressure turbine is good, and the weight and fatigue performance of the blade meet the requirements of the design drawings.

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

No PUM Login to View More

Abstract

The invention discloses a blade profile size control method, which comprises the following steps of: 1, selecting n blade sections from a blade tip of a blade to a joint of a blade body and a tenon root, namely S1, S2,... Sn, wherein n is a positive integer; 2, measuring the distance Hn from the section of each blade to the joint of the blade body and the tenon root; measuring the length H of thewhole blade body; 3, respectively substituting Hn and H into a formula; obtaining the offset Ln of the blade profile after the section Sn of the blade is subjected to wax mould placing and shrinking;wherein the maximum blade profile offset L of the joint of the blade body and the tenon root after wax mould placing and shrinking is a known amount; and 4, adopting the offset Ln to control the finaloffset of the section Sn of the blade when the blade is manufactured. The fatigue performance of the joint of the blade body and the tenon root is not reduced, the blade profile size design requirement and the blade weight requirement are met within the blade size tolerance range, and the blade cannot exceed the design weight.

Description

technical field [0001] The invention belongs to the field of engine blade manufacturing, and relates to a method for controlling blade profile size. Background technique [0002] The working blades of the aeroengine turbine are the rotating parts in the engine. They work in a very harsh environment. In order to improve the thrust-to-weight ratio of the engine, the weight of the working blades is required to fluctuate within a certain range; It has a certain fatigue strength. In addition to meeting the weight and fatigue performance, the blade size, especially the blade shape size, must also meet the requirements of the design drawings, and the tolerance requirements for the blade shape of the aeroengine turbine blade are very strict. Therefore, the working blade needs to be at the same time Satisfy the requirements of weight, fatigue performance and airfoil size. In the previous work blade airfoil size design, only the different shrinkage of the blade in the three-dimensiona...

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
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): B22C9/22B22C7/02G06F17/10
CPCB22C7/02B22C9/22G06F17/10
Inventor 朱珍珠王琳海潮常涛岐马李朝汪国峰闵蓉王斌
Owner AECC AVIATION POWER CO LTD