Adjusting device for thermal deformation correction of aero-engine turbine case

Abstract

The invention discloses an adjusting device for thermal deformation correction of an aero-engine turbine case, which comprises a base, a circle of fixing mechanism is arranged on the periphery of the top surface of the base in a surrounding manner, a circle of correction assembly is arranged on the inner side of the fixing mechanism in a surrounding manner, and a lifting lug bolt is further arranged on the top surface of the base. The recovery problem of turbine case deformation is solved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation repair, in particular to an adjustment device for thermal correction of deformation of a turbine casing of an aviation engine. Background Art

[0002] The turbine casing of an aircraft engine is an important load-bearing structural component designed to meet the needs of high-performance aircraft engines. The turbine casing is subjected to high temperatures and internal pressures, and transmits the axial force, torque, and vibration load of the engine. The high thrust-to-weight ratio of modern aircraft engines requires the casing to be light in weight. Reasonable material selection ensures that the parts can work safely and efficiently at high temperatures. It is necessary to ensure that the casing has sufficient rigidity, reduce the weight of the casing, and facilitate assembly with the rotor. The casings must have good thermal centering functions with each other, and the rotor and stator must maintain good concentricity. The most prominent problem of the turbine casing during use is deformation. The casing with a longitudinal mounting edge has uneven rigidity along the circumference, and the deformation is also uneven when heated and stressed, which is prone to ovality tolerance and warping deformation.

[0003] Before using an aircraft engine turbine casing, the distance from the trailing edge of the guide vane to the rear mounting edge of the casing and the axial clearance of the rotor and stator blades must be checked. If either of them does not meet the design requirements, the casing will be scrapped and replaced, which greatly increases the repair cost. Summary of the invention

[0004] The purpose of the present invention is to provide a device for adjusting the thermal shape of an aircraft engine turbine casing deformation, so as to solve the problem of restoring the turbine casing deformation.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions: A device for adjusting the deformation and thermal correction of an aircraft engine turbine casing comprises a base, a fixing mechanism is arranged around the periphery of the top surface of the base, a correction component is arranged around the inner side of the fixing mechanism, and the top surface of the base is also provided with ear bolts.

[0006] In this solution, the turbine casing is fixed to the base of the device through a fixing mechanism, and the diameter size of the turbine casing with larger deformation is quickly adjusted using the shaping assembly. The shaping device is hoisted into the heat treatment equipment for stabilization treatment by anchor bolts. The operation is simple and convenient, and the shaping size can be accurately controlled, which solves the problem of recovering from turbine casing deformation and ensures the effectiveness and stability of the product's size after thermal shaping.

[0007] As a further preferred embodiment of the present invention, the surface of the base is provided with screw holes, limiting ring grooves, fixing grooves and weight-reducing grooves.

[0008] The screw hole is used to connect the fixing mechanism, to connect the shape correction component, and to connect the ear bolt. The turbine casing is installed in the limiting ring groove. The fixing groove is used to connect with mechanical equipment. The weight-reducing groove is used to reduce the weight of the device.

[0009] As a further preferred embodiment of the present invention, the fixing mechanism includes an adjusting screw, a pressure plate, a hexagon socket head screw of the fixing mechanism and a flat washer. The adjusting screw is vertically arranged on the top surface of the base, the upper end of the adjusting screw is connected to the outer end of the pressure plate, the inner end of the pressure plate is pressed on the mounting edge of the turbine casing, the hexagon socket head screw of the fixing mechanism is downwardly passed through the long waist hole opened in the pressure plate part to press the pressure plate on the mounting edge of the turbine casing, and the flat washer is arranged between the screw head of the hexagon socket head screw of the fixing mechanism and the pressure plate.

[0010] The fixing mechanism is used to fasten the turbine casing to the device base, wherein the adjusting screw ensures that the pressure plate is flush with the surface of the turbine casing mounting edge, while the hexagon socket head screw of the fixing mechanism can press the pressure plate against the surface of the turbine casing.

[0011] As a further preferred embodiment of the present invention, the correction component includes a bracket, an adjusting screw, a nut, a baffle, a guide bolt and a fan-shaped top block. The bottom of the bracket is connected to the base through the hexagonal cylindrical head screw of the correction component. The adjusting screw is horizontally passed through the upper part of the bracket. The nut is arranged between the screw head of the adjusting screw and the inner end surface of the bracket. The baffle is arranged on the outer end surface of the bracket. The inner end of the baffle is connected to the adjusting screw, and the other end of the baffle is connected to the fan-shaped top block. The guide bolt is passed through the long waist hole of the baffle.

[0012] The adjusting screw rotates to push the baffle to move along the guide groove. The fan-shaped top block contacts the inner surface of the mounting edge on the turbine casing under the thrust of the baffle, and the diameter of the mounting edge is deformed under the action of the force. After the turbine casing is deformed, the adjusting screw is fixed by the nut.

[0013] As a further preferred embodiment of the present invention, there are three or more eye bolts. This provides higher stability during hoisting. Compared with the prior art, the present invention can achieve at least one of the following beneficial effects: 1. A calibration device is used to fix the turbine casing on a fixture, and the circumferentially distributed top columns are used to adjust the larger deformed ellipse to the roundness tolerance range required by the design. The dimension of the turbine casing remains stable after deformation through heat treatment. After natural aging, the deformed dimension of the part is checked to see if it has recovered. The conformity of the assembly dimension is tested to determine the stability of the dimension of the adjusted part, so that the part meets the assembly requirements of components and parts.

[0014] 2. The screw hole is used to connect the fixing mechanism, to connect the shape correction component, and to connect the ear bolt. The turbine casing is installed in the limiting ring groove. The fixing groove is used to connect with the mechanical equipment. The weight-reducing groove is used to reduce the weight of the device.

[0015] 3. More than three lifting eye bolts can make the lifting more stable. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the present invention.

[0017] Figure 2 It is a structural schematic diagram of the fixing mechanism of the present invention.

[0018] Figure 3 It is a schematic diagram of the structure of the shape correction component of the present invention. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0020] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0022] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0023] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use, or the positions or positional relationships commonly understood by those skilled in the art, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0024] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. Specific embodiment 1: Figure 1 , Figure 2 , Figure 3 A device for adjusting the deformation and thermal correction of an aircraft engine turbine casing is shown, comprising a base 1, a circle of fixing mechanisms 2 is arranged around the outer periphery of the top surface of the base 1, a circle of correction components 3 is arranged around the inner side of the fixing mechanisms 2, and a lifting eye bolt 4 is also arranged on the top surface of the base 1.

[0026] In this solution, the turbine casing is fixed to the base of the device through a fixing mechanism, and the diameter size of the turbine casing with larger deformation is quickly adjusted using the shaping assembly. The shaping device is hoisted into the heat treatment equipment for stabilization treatment by anchor bolts. The operation is simple and convenient, and the shaping size can be accurately controlled, which solves the problem of recovering from turbine casing deformation and ensures the effectiveness and stability of the product's size after thermal shaping. Specific embodiment 2: This embodiment further illustrates the base 1 on the basis of the specific embodiment 1. The surface of the base 1 is provided with screw holes, a limiting ring groove, a fixing groove and a weight-reducing groove.

[0028] The screw hole is used to connect the fixing mechanism, to connect the shape correction component, and to connect the ear bolt. The turbine casing is installed in the limiting ring groove. The fixing groove is used to connect with mechanical equipment. The weight-reducing groove is used to reduce the weight of the device. Specific embodiment 3: This embodiment further illustrates the fixing mechanism 2 on the basis of the specific embodiment 1, wherein the fixing mechanism 2 comprises an adjusting screw 21, a pressure plate 22, a fixing mechanism internal hexagon socket head screw 23 and a flat washer 24, wherein the adjusting screw 21 is vertically arranged on the top surface of the base 1, the upper end of the adjusting screw 21 is connected to the outer end of the pressure plate 22, the inner end of the pressure plate 22 is pressed on the mounting edge of the turbine casing, the fixing mechanism internal hexagon socket head screw 23 is downwardly passed through the long waist hole opened in the pressure plate 22 to press the pressure plate 22 on the mounting edge of the turbine casing, and the flat washer 24 is arranged between the screw head of the fixing mechanism internal hexagon socket head screw 23 and the pressure plate 22.

[0030] The fixing mechanism is used to fasten the turbine casing to the device base, wherein the adjusting screw ensures that the pressure plate is flush with the surface of the turbine casing mounting edge, while the hexagon socket head screw of the fixing mechanism can press the pressure plate against the surface of the turbine casing. Specific embodiment 4: This embodiment further illustrates the shape correction component 3 on the basis of the specific embodiment 1, and the shape correction component 3 includes a bracket 31, an adjusting screw 32, a nut 33, a baffle 34, a guide bolt 35 and a fan-shaped top block 36. The bottom of the bracket 31 is connected to the base 1 through a hexagonal cylindrical head screw 37 of the shape correction component. The adjusting screw 32 is horizontally penetrated through the upper part of the bracket 31, and the nut 33 is arranged between the screw head of the adjusting screw 32 and the inner end surface of the bracket 31. The baffle 34 is arranged on the outer end surface of the bracket 31, and the inner end of the baffle 34 is connected to the adjusting screw 32, and the other end of the baffle 34 is connected to the fan-shaped top block 36. The guide bolt 35 is penetrated through the long waist hole of the baffle 34.

[0032] The adjusting screw rotates to push the baffle to move along the guide groove. The fan-shaped top block contacts the inner surface of the mounting edge on the turbine casing under the thrust of the baffle, and the diameter of the mounting edge is deformed under the action of the force. After the turbine casing is deformed, the adjusting screw is fixed by the nut. Specific embodiment 5: This embodiment further illustrates the eye bolts 4 based on the specific embodiment 1, and there are more than three eye bolts 4.

[0034] More than three lifting eye bolts can make the lifting more stable.

[0035] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for adjusting the deformation and thermal correction of an aircraft engine turbine casing, characterized in that: The invention comprises a base (1), wherein a circle of fixing mechanisms (2) are arranged around the outer periphery of the top surface of the base (1), a circle of shape-correcting components (3) are arranged around the inner side of the fixing mechanisms (2), and a hanging eye bolt (4) is also arranged on the top surface of the base (1).

2. The device for adjusting the deformation and thermal correction of a turbine case of an aircraft engine according to claim 1, characterized in that: The surface of the base (1) is provided with screw holes, a limiting ring groove, a fixing groove and a weight-reducing groove.

3. The device for adjusting the deformation and thermal correction of an aircraft engine turbine casing according to claim 1, characterized in that: The fixing mechanism (2) comprises an adjusting screw (21), a pressure plate (22), a fixing mechanism internal hexagon socket head screw (23) and a flat washer (24); the adjusting screw (21) is vertically arranged on the top surface of the base (1); the upper end of the adjusting screw (21) is connected to the outer end of the pressure plate (22); the inner end of the pressure plate (22) is pressed on the mounting edge of the turbine casing; the fixing mechanism internal hexagon socket head screw (23) is downwardly passed through the long waist hole opened in the pressure plate (22) to press the pressure plate (22) on the mounting edge of the turbine casing; the flat washer (24) is arranged between the screw head of the fixing mechanism internal hexagon socket head screw (23) and the pressure plate (22).

4. The device for adjusting the deformation and thermal correction of an aircraft engine turbine casing according to claim 1, characterized in that: The shape correction component (3) comprises a bracket (31), an adjusting screw (32), a nut (33), a baffle (34), a guide bolt (35) and a fan-shaped top block (36). The bottom of the bracket (31) is connected to the base (1) through a hexagon socket head screw (37) of the shape correction component. The adjusting screw (32) is horizontally inserted into the upper part of the bracket (31). The nut (33) is arranged between the screw head of the adjusting screw (32) and the inner end surface of the bracket (31). The baffle (34) is arranged on the outer end surface of the bracket (31). The inner end of the baffle (34) is connected to the adjusting screw (32). The other end of the baffle (34) is connected to the fan-shaped top block (36). The guide bolt (35) is inserted into the long waist hole of the baffle (34).

5. The device for adjusting the deformation and thermal correction of a turbine case of an aircraft engine according to claim 1, characterized in that: There are three or more eye bolts (4).

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