Aero-engine high-pressure turbine disc and shaft connecting structure

Abstract

The application belongs to the technical field of aero-engines, and particularly relates to a high-pressure turbine disc and shaft connecting structure of an aero-engine, which comprises a high-pressure turbine disc, a high-pressure turbine shaft, bolts and self-locking nuts. The high-pressure turbine disc has a high-pressure turbine disc support arm formed by axial extension, and the end of the high-pressure turbine disc support arm has a high-pressure turbine disc flange edge extending radially outward. The high-pressure turbine shaft has a flange plate, and the outer edge of the flange plate has a stop cylinder surface in contact with the end of the high-pressure turbine disc flange edge for limiting. The bolts pass through the mounting holes of the flange plate and the mounting edge and are connected with the self-locking nuts, so that the high-pressure turbine shaft and the high-pressure turbine disc are fixedly connected. The application can improve stress distribution. Temperature stress is distributed on the high-pressure turbine disc, centrifugal stress is distributed on the support arm of the high-pressure turbine disc, and bending stress is distributed on the bending part of the high-pressure turbine shaft return structure. The concentrated stress at the root of the high-pressure turbine disc flange is shared by different parts, and the reliability of flight safety is improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engines, and particularly relates to a high-pressure turbine disc and shaft connecting structure of an aero-engine. BACKGROUND

[0002] The working environment of a high-pressure turbine rotor of an aero-engine has the characteristics of high temperature, high pressure and high speed. The turbine inlet temperature of a high-performance aero-engine currently exceeds 2100K, the turbine inlet gas total pressure exceeds 20 atmospheres, and the maximum rotational speed is above 10000r / min. The high-pressure turbine rotor is simultaneously affected by temperature load, aerodynamic load, centrifugal load and bending load when working, and bears extremely high load.

[0003] Under such high load conditions, if stress concentration exists between the high-pressure turbine disc and the high-pressure turbine shaft, or the robustness and reliability are poor, the connecting stiffness of the high-pressure turbine rotor and the contact state of the connecting surface will be seriously affected, which will further affect the overall dynamics, vibration characteristics and safety of the aero-engine.

[0004] At present, the most widely used connecting structure between the high-pressure turbine disc and the high-pressure turbine shaft is the flange-bolt connecting structure, which is connected in the manner of stopper cylindrical surface centering, end surface bearing and bolt compression.

[0005] The disadvantages of the prior art include:

[0006] 1) Stress concentration exists: the root of the high-pressure turbine disc flange is a concentration area of temperature stress, centrifugal stress and bending stress, and high-pressure turbine disc strength failure is easy to occur, which endangers flight safety;

[0007] 2) Poor connection robustness: under the action of centrifugal load and bending moment, the high-pressure turbine disc and the high-pressure turbine shaft deform uncoordinately, which easily leads to the "opening" of the stopper cylindrical surface for centering, local separation, and slip and wear on the bolt fitting interface, so that the overall vibration amplitude increases. SUMMARY

[0008] In order to solve the above problems, the application provides a high-pressure turbine disc and shaft connecting structure of an aero-engine, which comprises:

[0009] a high-pressure turbine disc, a high-pressure turbine shaft, a bolt and a self-locking nut;

[0010] The high-pressure turbine disc has an axially extending high-pressure turbine disc support arm, and the end of the high-pressure turbine disc support arm has a radially outward high-pressure turbine disc flange edge.

[0011] The high-pressure turbine shaft has a flange plate, the outer edge of the flange plate has a stop cylinder surface in contact with the end of the flange edge of the high-pressure turbine disc; the bolt passes through the mounting hole of the flange plate and the mounting edge and is connected with the self-locking nut, so that the high-pressure turbine shaft and the high-pressure turbine disc are fixedly connected.

[0012] Preferably, the flange plate of the high-pressure turbine shaft has a turn-back structure, which includes a straight wall in the middle of the flange plate and an outer inclined wall and an inner inclined wall on the radial outer side and the radial inner side of the straight wall; the wall surface of the straight wall is perpendicular to the axis of the high-pressure turbine shaft, and the wall surfaces of the outer inclined wall and the inner inclined wall have an included angle with the wall surface of the straight wall.

[0013] Preferably, the contact surface of the flange edge of the high-pressure turbine disc and the flange plate is a plane, which is perpendicular to the axis of the high-pressure turbine shaft.

[0014] Preferably, the support arm of the high-pressure turbine disc is in the shape of a cylinder.

[0015] Preferably, the cylindrical high-pressure turbine disc support arm has circumferentially distributed open grooves, which provide a circumferential and radial deformation allowance.

[0016] Preferably, during installation, the high-pressure turbine disc is cooled by liquid nitrogen.

[0017] The application has the following advantages:

[0018] 1) The stress distribution is improved. The temperature stress is distributed on the high-pressure turbine disc, the centrifugal stress is distributed on the support arm of the high-pressure turbine disc, and the bending stress is distributed at the bending position of the turn-back structure of the high-pressure turbine shaft. The concentrated stress at the root of the flange of the high-pressure turbine disc is dispersed to different parts, thereby improving the overall structural strength, avoiding damage to the high-pressure turbine disc, and improving the reliability of flight safety.

[0019] 2) The robustness of the connection structure is improved. The centrifugal stress, the temperature stress, and the bending stress are distributed on the structure other than the bolt connection, so that the relative rigidity of the bolt connection structure is high, and excessive deformation does not occur, thereby avoiding connection strength failure. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a schematic diagram of the connection structure of the high-pressure turbine disc and the shaft of the preferred embodiment of the application. DETAILED DESCRIPTION

[0021] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0022] like Figure 1 As shown, this application provides a high-pressure turbine disk and shaft connection structure for an aero-engine, comprising:

[0023] 1. High-pressure turbine disk; 2. High-pressure turbine shaft; 3. Bolt and 4. Self-locking nut;

[0024] The high-pressure turbine disk 1 has an axially extended high-pressure turbine disk support arm 1-1, and the end of the high-pressure turbine disk support arm 1-1 has a radially outward high-pressure turbine disk flange edge 1-2.

[0025] The high-pressure turbine shaft 2 has a flange, and the outer edge of the flange has a stop cylindrical surface M that contacts and limits the end of the flange edge 1-2 of the high-pressure turbine disk; the bolt 3 passes through the mounting hole of the flange and the mounting edge and connects with the self-locking nut 4 to fix the high-pressure turbine shaft 2 to the high-pressure turbine disk 1.

[0026] During installation, liquid nitrogen is used to cool the high-pressure turbine disk 1. After the high-pressure turbine disk 1 cools down to a certain level and contracts, the high-pressure turbine shaft 2 is assembled onto the flange edge of the high-pressure turbine disk 1. Note that during assembly, it is necessary to ensure that the bolt holes on the high-pressure turbine disk 1 and the high-pressure turbine shaft 2 correspond one-to-one in the angular direction. After the high-pressure turbine disk 1 returns to normal temperature, the high-pressure turbine disk 1 and the high-pressure turbine shaft 2 can be centered by means of the locating cylindrical surface M. The bolts 3 are passed through the flange holes on the high-pressure turbine shaft 2 and the high-pressure turbine disk 1, and the tightening torque is applied to the self-locking nut 4 to axially press the high-pressure turbine disk 1 and the high-pressure turbine shaft 2 together, ensuring that the high-pressure turbine disk 1 and the high-pressure turbine shaft 2 are in contact with the plane N, which is perpendicular to the axis of the high-pressure turbine shaft 2.

[0027] In some alternative embodiments, the flange of the high-pressure turbine shaft 2 has a folding structure 2-1, which includes a straight wall 2-1a located in the middle of the flange, an outer inclined wall 2-1b located radially outward of the straight edge, and an inner inclined wall 2-1c located radially inward; the wall surface of the straight wall 2-1a is perpendicular to the axis of the high-pressure turbine shaft 2, and the wall surfaces of the outer inclined wall 2-1b and the inner inclined wall 2-1c have an angle with the wall surface of the straight wall 2-1a.

[0028] In some alternative embodiments, the high-pressure turbine disc support arm 1-1 is cylindrical in shape. The cylindrical high-pressure turbine disc support arm 1-1 has circumferentially distributed open slots, providing circumferential and radial deformation allowance.

[0029] The advantages of the present application include: 1. The axial lengthening of the high-pressure turbine disc support arm 1-1 and the radial lifting of the high-pressure turbine disc flange edge 1-2 structure reduces the centrifugal load deformation difference between the high-pressure turbine disc 1 and the high-pressure turbine shaft 2, reduces the additional stress at the high-pressure turbine disc 1 mounting point, and the centrifugal stress is more evenly distributed on the high-pressure turbine disc support arm 1-1;

[0030] 2. The angular stiffness at the bend of the return structure 2-1 on the high-pressure turbine shaft 2 is low, and under the action of bending moment, this place is a bending stress concentration area, which will not have a large impact on the bearing inner ring, thereby reducing the dynamic load at bearing P and improving the bearing service life;

[0031] 3. The temperature stress, centrifugal stress and bending stress are distributed on the structure outside the bolt connections 3 and 4, the concentrated stress on the high-pressure turbine disc flange edge 1-2 is dispersed to different parts, thereby improving the overall structural strength, avoiding excessive deformation and connection strength failure, and improving the connection structure robustness.

[0032] 4. The high-pressure turbine disc support arm 1-1 with open slots has a certain elasticity on the one hand, and provides a certain thermal deformation allowance for the high-pressure turbine disc support arm 1-1 on the other hand.

[0033] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any changes or replacements within the technical scope disclosed in the present application can be easily thought of by those skilled in the art, and should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A high-pressure turbine disk and shaft connection structure for an aero-engine, characterized in that, include: High-pressure turbine disk (1), high-pressure turbine shaft (2), bolt (3) and self-locking nut (4); The high-pressure turbine disk (1) has an axially extended high-pressure turbine disk support arm (1-1) and a radially outward high-pressure turbine disk flange edge (1-2) at the end of the high-pressure turbine disk support arm (1-1). The high-pressure turbine shaft (2) has a flange, and the outer edge of the flange has a stop cylindrical surface (M) that contacts and limits the end of the flange edge (1-2) of the high-pressure turbine disk; the bolt (3) passes through the mounting hole of the flange and the mounting edge and is connected to the self-locking nut (4) to fix the high-pressure turbine shaft (2) to the high-pressure turbine disk (1); The flange of the high-pressure turbine shaft (2) has a folding structure (2-1). The folding structure (2-1) includes a straight wall (2-1a) located in the middle of the flange, an outer inclined wall (2-1b) located radially outside the straight wall (2-1a), and an inner inclined wall (2-1c) located radially inside the straight wall (2-1a). The wall surface of the straight wall (2-1a) is perpendicular to the axis of the high-pressure turbine shaft (2), and the wall surfaces of the outer inclined wall (2-1b) and the inner inclined wall (2-1c) have an angle with the wall surface of the straight wall (2-1a).

2. The connection structure between the high-pressure turbine disk and the shaft of an aero-engine as described in claim 1, characterized in that, The contact surface between the high-pressure turbine disk flange edge (1-2) and the flange is a plane (N), which is perpendicular to the axis of the high-pressure turbine shaft (2).

3. The connection structure between the high-pressure turbine disk and the shaft of an aero-engine as described in claim 1, characterized in that, The high-pressure turbine disk support arm (1-1) is cylindrical in shape.

4. The connection structure between the high-pressure turbine disk and the shaft of an aero-engine as described in claim 3, characterized in that, The cylindrical high-pressure turbine disk support arm (1-1) has circumferentially distributed opening slots to provide circumferential and radial deformation allowances.

5. The connection structure between the high-pressure turbine disk and the shaft of an aero-engine as described in claim 3, characterized in that, During installation, the high-pressure turbine disk (1) is cooled by liquid nitrogen.

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