CN102787868A

CN102787868A - Method for controlling stress of aircraft engine turbine disk based on active temperature gradient

Info

Publication number: CN102787868A
Application number: CN2012102175444A
Authority: CN
Inventors: 丁水汀; 李果; 杜发荣; 刘晓静; 鲍梦瑶
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2012-06-27
Filing date: 2012-06-27
Publication date: 2012-11-21

Abstract

The invention relates to a method for controlling stress of an aircraft engine turbine disk based on an active temperature gradient, so as to effectively reduce the stress on the turbine disk. The invention provides the method for controlling the stress of the aircraft engine turbine disk based on the active temperature gradient. The method is characterized in that a core of the turbine disk is heated actively so as to increase the temperature of the core area; as the temperature of the core area of the turbine disk is increased, a reverse temperature gradient is constructed between the core of the turbine disk and a radial plate; and the reverse temperature gradient generates a pulling action on the stress level of the turbine disk. The maximum stress level on the turbine disk drops 25% more than the maximum stress level on the traditional turbine disk under the same operating condition due to the pulling action of the reverse temperature gradient between the core of the turbine disk and the radial plate, and the stress level on the turbine disk can be controlled without traditionally increasing the geometric dimension of a danger area or optimizing a structure, so that a new method is provided for controlling the stress level on the turbine disk.

Description

A kind of method based on active temperature gradient control aero-engine turbine disk stress

Technical field

The present invention relates to a kind of aero-engine turbine disk stress control method based on the control of active temperature gradient; Specifically through the aero-engine turbine disk core initiatively being heated to improve the mode of core regional temperature; Between turbine disk core and disc, set up reverse temperature gradient; The pulling function of utilizing reverse temperature gradient to produce reaches the purpose of alleviating turbine disk upper stress.

Background technique

The turbine disk is one of core component of aeroengine, is bearing combustion gas is promoted turbine blade institute work to be passed to axle to drive the task of parts work such as fan, gas compressor, generator.Working environment that it is intrinsic and work characteristics can be summarized as follows:

1. the turbine disk is positioned at after the firing chamber; Its thermal environment is extremely severe; Temperature on the present high-performance aero-engine turbine disk has surpassed 1000K, and under this temperature environment, the strength character of turbine disk material will sharply descend; Thereby can not satisfy the requirement of life-span and reliability, so often the turbine disk is cooled off.

2. the working speed of the turbine disk generally surpasses 10000rpm, therefore bears great centrifugal load; Owing to, so relate to complicated on the turbine disk and thermal stress load that constantly change with operating conditions to the cooling of the turbine disk and the skewness of thermal environment.So the stress levels overall on the turbine disk is very high.

Just because of above characteristics, the turbine disk also is one of the most dangerous parts of aeroengine, normally guarantees reliable strength demand through the physical dimension that increases the deathtrap with the stress level on the control turbine disk.Therefore at present typical turbine disc structure form is: the thickening of physical dimension is adopted in the maximum core zone of turbine disk stress level; The thickness of turbine disk web area radially gradually attenuation to alleviate quality, because the stress level characteristic distributions on the turbine disk radially reduces gradually; Turbine disk dish edge zone is thickening gradually once more, because the tension that the dish edge must bear blade.It should be noted that to increase the increase that physical dimension will directly cause turbine disk quality, and modern advanced aeroengine is not encouraged so increase physical dimension because the high thrust weight ratio of pursuit is very responsive to quality.For alleviating as far as possible since the increase of the turbine disk quality that proof strength is brought after the geometric shape of the turbine disk is roughly confirmed, need do further adjustment through Optimal Structure Designing, thereby between the stress level of the turbine disk and quality, keep balance.

Can find out; Mode to turbine disk Stress Control is more single; And unsatisfactory from its effect of present aeroengine: the difficult quality of the turbine disk significantly reduces under the prerequisite of proof strength, thereby directly affects the further lifting of thrust weight ratio; Still the turbine disk that higher stress level the brings main cause of aircraft catastrophic failure often of breaking, lost efficacy also.Therefore, must control the stress on the turbine disk through other technological means.

Summary of the invention

The objective of the invention is to provide a kind of aero-engine turbine disk stress control method based on the control of active temperature gradient, it can effectively alleviate the stress on the turbine disk.

The invention provides a kind of aero-engine turbine disk stress control method, it is characterized in that: initiatively to the temperature of turbine disk core heating with raising core zone based on the control of active temperature gradient; Because reverse temperature gradient is constructed in the raising of turbine disk core regional temperature between turbine disk core and disc; This reverse temperature gradient produces pulling function to turbine disk stress level.

The invention has the advantages that: (1) is through the pulling function of reverse temperature gradient between turbine disk core and disc; Under identical operating conditions condition; Maximum stress level on the turbine disk is compared decline does not need traditional passing through increase deathtrap physical dimension and control turbine disk upper stress level through Optimal Structure Designing with the conventional turbine dish above 25% (2), for the control of the stress level on the turbine disk provides a kind of new method.

Description of drawings

Fig. 1 typical case aero-engine turbine disk adopts active temperature gradient proof stress method schematic representation;

Fig. 2 active temperature gradient control turbine disk and conventional turbine dish temperature field cloud charts contrast schematic representation;

Fig. 3 active temperature gradient control turbine disk and conventional turbine dish temperature field distribution curve contrast schematic representation;

Fig. 4 active temperature gradient control turbine disk and conventional turbine disk stress cloud charts contrast schematic representation.

More than among the figure: 1. conventional turbine dish; 2. the active temperature gradient is controlled the turbine disk; 3. the dish edge heats hot-fluid;

4. core is regional; 5. web area; 6. the dish edge is regional; 7. core heats hot-fluid;

8. turbine disk chamber; 9. reverse temperature gradient.

Embodiment

To combine accompanying drawing that the present invention is done further detailed description below.Referring to shown in Figure 1.The active temperature gradient control turbine disk 2 also increases at turbine disk core and introduces the 7 initiatively heating of core heating hot-fluid, to improve the temperature in core zone 4 except that the heat effect that receives dish edge heating hot-fluid 3.Because the rising of core regional temperature; Change dish edge zone 6 temperature height on the conventional turbine dish 1; The temperature distribution form that the core regional temperature is low is that core is high with dish edge regional temperature; The temperature distribution form (as shown in Figure 2) that web area 5 temperature are low is promptly set up reverse temperature gradient 9 (as shown in Figure 3) between core zone and web area.The pulling function of utilizing reverse temperature gradient to produce is gone to offset the centrifugal force that partial rotation produces, thereby is effectively alleviated the maximum stress level on the turbine disk.

Thus, through the pulling function of reverse temperature gradient between core and disc, the maximum stress level on the turbine disk is compared with the conventional turbine dish to descend and is surpassed 25% (as shown in Figure 4).This temperature gradient control turbine disk is not controlled turbine disk upper stress level through traditional increase deathtrap physical dimension and through Optimal Structure Designing, for the control of the stress level on the turbine disk provides a kind of new method.

Claims

1. method based on active temperature gradient control aero-engine turbine disk stress; It is characterized in that: aero-engine turbine disk is except that the heat effect that receives dish edge heating hot-fluid (3); Also introduce core heating hot-fluid (4) and carry out active heating, with the temperature that improves core zone (7) and between core regional (7) and web area (6), set up reverse temperature gradient (9) at turbine disk core.This reverse temperature gradient produces pulling function to turbine disk stress level, thereby alleviates suffered stress on the turbine disk.