CN103046964B

CN103046964B - A kind of aero-engine turbine disk based on active temperature gradient proof stress

Info

Publication number: CN103046964B
Application number: CN201210218772.3A
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: 2015-12-09
Anticipated expiration: 2032-06-27
Also published as: CN103046964A

Abstract

The present invention provides a kind of aero-engine turbine disk controlled based on active temperature gradient, and it has lower stress level and less quality compared with conventional turbine dish.The invention provides a kind of aero-engine turbine disk based on active temperature gradient proof stress, turbine disk core place arranges heating chamber, introduces heated air to hub area active heated to set up reverse temperature gradient between core and disc in heating chamber; Turbine disk disc being opened interior stream chamber to increase the temperature gradient between core and disc, is air in interior stream chamber.By the pulling function of temperature gradient reverse between core and disc, under identical operating conditions condition, the maximum stress level on the turbine disk decrease beyond 4.5% compared with conventional turbine dish; The turbine disk is opened heating chamber and interior stream chamber, turbine disk overall weight can be made to decrease beyond 7.4%; Do not need traditional by increasing deathtrap physical dimension and controlling turbine disk upper stress level by Optimal Structure Designing, thus obtain a kind of between stress level and quality the better turbine disk of balance.

Description

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

Technical field

The present invention relates to a kind of aero-engine turbine disk based on active temperature gradient proof stress, specifically open heating chamber at aeroengine core, web area opens the mode in interior stream chamber, reaches the stress level alleviated on the turbine disk, alleviates the object of turbine disk quality.

Background technique

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

1. after the turbine disk is positioned at firing chamber, its thermal environment is extremely severe, temperature on the current High Performance Aeroengine turbine disk has exceeded 1000K, under this temperature environment, the strength character of turbine disk material will sharply decline, thus the requirement of life-span and reliability can not be met, so often the turbine disk is cooled.

2. the working speed of the turbine disk is generally more than 10000rpm, therefore bears great centrifugal load; Due to the cooling of the turbine disk and the skewness of thermal environment, therefore the turbine disk relates to the complicated and thermal stress load constantly changed with operating conditions.So the stress levels overall on the turbine disk is very high.

Just because of above feature, the turbine disk is also one of the most dangerous parts of aeroengine, and the physical dimension normally by increasing deathtrap ensures reliable strength demand with the stress level controlled on the turbine disk.Therefore typical turbine disk form is at present: the thickening of the hub area employing physical dimension that turbine disk stress level is maximum; The thickness of turbine disk web area is radially thinning to alleviate quality gradually, because the stress level characteristic distributions on the turbine disk radially reduces gradually; Turbine disk dish edge region thickeies again gradually, because dish edge must bear the pulling force effect of blade.It should be noted that increasing physical dimension will directly cause the increase of turbine disk quality, and modern advanced aero engine is owing to pursuing high thrust weight ratio, very responsive to quality, do not encouraged so increase physical dimension.For the increase of the turbine disk quality that alleviation of trying one's best brings due to proof strength, after the geometric shape of the turbine disk is roughly determined, further adjustment need be done by Optimal Structure Designing, thus maintain balance between the stress level and quality of the turbine disk.

Can find out, more single to the mode of turbine disk stress level and quality control, and unsatisfactory from its effect of current aeroengine: the difficult quality of the turbine disk significantly reduces under the prerequisite of proof strength, thus directly affects the further lifting of thrust weight ratio; Still the turbine disk that higher stress level brings breaks, the main cause of the aircraft catastrophic failure often of losing efficacy also.Therefore, the stress level on the turbine disk must be controlled by other technological means, reduce turbine disk quality.

Summary of the invention

The object of the invention is to provide a kind of aero-engine turbine disk controlled based on active temperature gradient, it effectively can be alleviated the stress level on the turbine disk and reduce the quality of the turbine disk simultaneously.

The invention provides a kind of aero-engine turbine disk based on active temperature gradient proof stress, it is characterized in that: turbine disk core place arranges heating chamber, in heating chamber, introduce heated air to hub area active heated to set up reverse temperature gradient between core and disc; Turbine disk disc being opened interior stream chamber to increase the temperature gradient between core and disc, is air in interior stream chamber.

The invention has the advantages that: (1), by the pulling function of temperature gradient reverse between core and disc, under identical operating conditions condition, the maximum stress level on the turbine disk decrease beyond 4.5% compared with conventional turbine dish; (2) turbine disk is opened heating chamber and interior stream chamber, turbine disk overall weight can be made to decrease beyond 7.4%; (3) do not need traditional by increasing deathtrap physical dimension and controlling turbine disk upper stress level by Optimal Structure Designing, thus obtain a kind of between stress level and quality the better turbine disk of balance.

Accompanying drawing explanation

Fig. 1 active temperature gradient controls turbine disk schematic diagram;

Fig. 2 active temperature gradient controls the turbine disk and conventional turbine dish thermo parameters method cloud atlas contrasts schematic diagram;

Fig. 3 active temperature gradient controls the turbine disk and conventional turbine dish thermo parameters method curve comparison schematic diagram;

Fig. 4 active temperature gradient controls the turbine disk and conventional turbine disk stress cloud charts contrasts schematic diagram.

In above figure: 1. active temperature gradient controls the turbine disk; 2. stream chamber in; 3. heating chamber; 4. heated air; 5. coil edge region; 6. web area; 7. hub area; 8. conventional turbine dish; 9. turbine disk dish chamber.

Embodiment

Below in conjunction with accompanying drawing, the present invention is described in further detail.Shown in Figure 1.Open heating chamber 3 in turbine disk hub area 7, introduce heated air 4 and enter heating chamber to complete the active heated to hub area.Due to the rising of hub area temperature, change conventional turbine dish coils edge region 5 temperature high, the temperature distribution form that hub area temperature is low is that core is high with dish edge regional temperature, the temperature distribution form (as shown in Figure 2) that disc temperature is low, namely sets up reverse temperature gradient (as shown in Figure 3) between core and disc 6.The pulling function utilizing reverse temperature gradient to produce, goes to offset part and rotates the centrifugal force produced, thus the effective maximum stress level alleviated on the turbine disk.Obviously, reverse temperature gradient is larger, and that brings is more remarkable to the mitigation of the upper maximum stress level of dish.Therefore, turbine disk disc being opened interior stream chamber 2, is air in interior stream chamber.Because the thermal conductivity of gas is less than metal, so the existence in stream chamber increases the thermal conduction resistance of web area inherently, thus increase the reverse temperature gradient on the turbine disk further, namely increase the mitigation of counter stress level.

Thus, by the pulling function of temperature gradient reverse between core and disc, under identical operating conditions condition, the maximum stress level on the turbine disk decrease beyond 4.5% compared with conventional turbine dish.The turbine disk is opened heating chamber and interior stream chamber, overall Quality Down can be made more than 7.4%.This temperature gradient controls the turbine disk and does not control turbine disk upper stress level by traditional increase deathtrap physical dimension and by Optimal Structure Designing, thus obtains one better turbine disk of balance between stress level and quality.

Claims

1. the aero-engine turbine disk based on active temperature gradient proof stress, it is characterized in that: heating chamber (3) is set at turbine disk core (7) place, in described heating chamber (3), introduce heated air (4) to described turbine disk hub area active heated to set up reverse temperature gradient between turbine disk core and turbine disk disc; Described turbine disk disc (6) arranging interior stream chamber (2) to increase the temperature gradient between turbine disk core and turbine disk disc, is air in described interior stream chamber; By the pulling function of temperature gradient reverse between core and disc, the maximum stress level on the turbine disk decrease beyond 4.5% compared with conventional turbine dish; The described heating chamber (3) that the turbine disk is arranged and described interior stream chamber (2), make turbine disk overall weight decrease beyond 7.4%.