Aero-engine high-pressure turbine six-blade inner diameter testing fixture

Abstract

The utility model discloses aeroengine high pressure turbine six association blade inner diameter testing fixture, including base, the upper end of base is equipped with positioning assembly, positioning assembly includes the first locating block, second locating block and third locating block of fixed connection in the upper end of base, the first locating block and second locating block are located left side, third locating block is located right side, be equipped with measuring assembly on the base, measuring assembly includes two fixed blocks of fixed connection on the base, two all are equipped with measuring block on two fixed blocks, the upper end of two measuring block all is equipped with three measuring holes and a zero hole, the utility model discloses can realize the quick inspection of aeroengine multi-association blade's inner diameter size, effectively filters out the size of the out-of-tolerance part, avoids the rework waste caused by the unqualified final size. In addition, the testing fixture can also be used to measure the size of the reshaped unqualified parts, prevent the reshaping amount too small or too large, thereby guaranteeing the reshaping qualification rate, improving production efficiency.

Description

Technical Field

[0001] This utility model relates to the field of investment casting technology, and in particular to a gauge for the inner diameter of six-blade high-pressure turbines for aero-engines. Background Technology

[0002] The multi-stage blades of a high-pressure turbine in an aero-engine are a core component. The accuracy of their inner diameter directly determines the fit quality between the component and the rotor shaft, which has a crucial impact on the overall performance, safety, and reliability of the engine. If this dimension deviates from the tolerance, it can lead to a series of serious consequences, such as a loose fit causing vibration or a tight fit preventing assembly.

[0003] Currently, the inspection of the inner diameter of multi-unit blades in production relies heavily on coordinate measuring machines (CMMs) or general-purpose measuring tools. CMMs are inefficient and costly, failing to meet the needs of rapid on-site inspection. General-purpose measuring tools, on the other hand, suffer from inconsistent benchmarks, cumbersome operation, and discrete measurement data, making it impossible to quickly and accurately screen parts. This leads to out-of-tolerance parts flowing into subsequent processes, only to be discovered during final dimensional inspection, resulting in significant rework waste. Furthermore, during rework and shaping, the lack of effective means to measure precise shaping amounts easily leads to improper shaping, causing repeated rework or direct scrapping of parts, severely restricting production efficiency and product qualification rates.

[0004] Therefore, it is necessary to design a six-piece blade inner diameter gauge for high-pressure turbines in aero-engines to solve the above problems. Utility Model Content

[0005] The technical problem this utility model aims to solve is: addressing the issues of low efficiency, difficulty in guaranteeing accuracy, and inability to accurately measure rework and reshaping quantities in existing technologies for inspecting the inner diameter of multi-stage blades. This utility model provides a special inspection tool designed to achieve rapid and accurate inspection of the inner diameter dimensions of multi-stage blades and to provide precise quantitative basis for rework and reshaping.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: A six-blade inner diameter gauge for high-pressure turbines for aero-engines includes a base. A positioning assembly is located on the upper end of the base. The positioning assembly includes a first positioning block, a second positioning block, and a third positioning block fixedly connected to the upper end of the base. The first and second positioning blocks are located on the left side, and the third positioning block is located on the right side. A measuring assembly is located on the base, including two fixed blocks fixedly connected to the base. Each of the two fixed blocks has a measuring block. Each of the two measuring blocks has three measuring holes and one zeroing hole at its upper end. The third positioning block is located between the two fixed blocks. The first and second positioning blocks have multiple first reference point positioning pins, and the upper end of the third positioning block has a second reference point positioning pin.

[0007] Preferably, the rear side of the first positioning block is provided with a rectangular groove, the left side wall of the rectangular groove is provided with a stepped protrusion, the connection between the stepped protrusion and the rectangular groove is rounded, the upper end of the first positioning block is a plane, and a plurality of first reference point positioning pins are respectively located above the first positioning block, to the right of the stepped protrusion and behind the first positioning block.

[0008] Preferably, the left side of the second positioning block is provided with an arc-shaped groove, and the left side of the second positioning block is a stepped protrusion, with a plurality of first reference point positioning pins located on the right side of the stepped protrusion above the second positioning block.

[0009] Preferably, the third positioning block is U-shaped, and a second locking bolt is threaded through the right side of the third positioning block.

[0010] Preferably, the upper ends of the two fixing blocks and the measuring block are provided with threaded holes, and a first locking bolt is threadedly connected to each pair of mating threaded holes.

[0011] Preferably, slide rails are fixedly connected to the opposite sides of the two fixed blocks, and fixed plates are slidably connected to the two slide rails. The two fixed plates are fixedly connected to the corresponding measuring blocks.

[0012] Compared with existing technologies, the advantages of this device are: Compared with existing technologies, the differentiated structural design of the first, second, and third positioning blocks, combined with multiple sets of reference point positioning pins, forms a three-point collaborative positioning mechanism. The stepped protrusions and rounded corners of the first positioning block, the arc-shaped grooves and stepped extensions of the second positioning block, and the locking bolts of the U-shaped third positioning block can accurately fit the complex shape of the six-piece blade, avoiding positioning deviations and solving the problems of single positioning and poor adaptability of traditional inspection tools. Compared with existing technologies, the measuring component adopts a sliding fit structure of slide rail and fixed plate, combined with the detachable connection design of the first locking bolt, which allows for quick adjustment of the measuring block position. A single measuring block integrates three measuring holes and one zeroing hole, enabling simultaneous acquisition and calibration of multiple sets of inner diameter data. Compared with the traditional method of single measurement and multiple calibrations, this significantly improves the detection efficiency and is suitable for the measurement needs of six-blade units of different specifications. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of the six-unit blade inner diameter gauge for high-pressure turbines proposed in this utility model. Figure 2 This is a structural schematic diagram of the six-blade inner diameter gauge for high-pressure turbines proposed in this utility model from another perspective. Figure 3 This is a top-view structural diagram of the six-blade inner diameter inspection fixture for high-pressure turbines proposed in this utility model.

[0014] In the diagram: 1 base, 2 first positioning block, 3 second positioning block, 4 third positioning block, 5 fixing block, 6 measuring block, 7 slide rail, 8 fixing plate, 9 first locking bolt, 10 measuring hole, 11 zeroing hole, 12 first reference point positioning pin, 13 second reference point positioning pin, 14 second locking bolt. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0016] Reference Figures 1-3 This is a six-unit blade inner diameter gauge for high-pressure turbines used in aero-engines. It includes a base 1, which is a rigid flat plate structure. The upper surface of the base 1 is milled to ensure flatness, providing a stable mounting reference for the positioning and measuring components. A positioning component is located at the upper end of the base 1. This component includes a first positioning block 2, a second positioning block 3, and a third positioning block 4, fixedly connected to the upper end of the base 1. These three blocks are arranged in a triangular pattern to form a stable support and positioning structure. The first positioning block 2 and the second positioning block 3 are spaced apart along the left edge of the base 1, while the third positioning block 4 is located at the middle right side of the base 1. The first positioning block 2 and the second positioning block 3 are located on the left side, and the third positioning block 4 is located on the right side of the base 1. 4 is located on the right side. The base 1 is equipped with a measuring component. The measuring component includes two fixed blocks 5 fixedly connected to the base 1. Each of the two fixed blocks 5 is equipped with a measuring block 6. The two measuring blocks 6 can be adjusted in a preset direction to accurately align with the blade detection area. Each of the two measuring blocks 6 has three measuring holes 10 and one zeroing hole 11 at its upper end. The zeroing hole 11 is located on one side of the three measuring holes 10 and is used for calibration before measurement. The third positioning block 4 is located between the two fixed blocks 5. The first positioning block 2 and the second positioning block 3 are equipped with multiple first reference point positioning pins 12. The upper end of the third positioning block 4 is equipped with a second reference point positioning pin 13.

[0017] The first positioning block 2 has a rectangular groove on its rear side, and a stepped protrusion on the left side wall of the rectangular groove. The connection between the stepped protrusion and the rectangular groove is rounded. Each step surface of the stepped protrusion is a positioning reference surface and fits and matches the contour of the corresponding part of the blade. The upper end of the first positioning block 2 is a plane. Multiple first reference point positioning pins 12 are located above the first positioning block 2, to the right of the stepped protrusion, and behind the first positioning block 2, respectively. The second positioning block 3 has an arc-shaped groove on its left side and a stepped protrusion on its left side. Multiple first reference point positioning pins 12 are located to the right of the stepped protrusion above the second positioning block 3, respectively. The third positioning block 4 is U-shaped. A second locking bolt 14 is threaded through the right side of the third positioning block 4. An elastic washer is provided at the inner end of the second locking bolt 14. Rotating the second locking bolt 14 can push the elastic washer to press against the side of the blade, thereby achieving a stable clamping of the blade.

[0018] The upper ends of the two fixing blocks 5 and the measuring block 6 are provided with threaded holes. A first locking bolt 9 is threadedly connected to each pair of mating threaded holes. Slide rails 7 are fixedly connected to the opposite sides of the two fixing blocks 5. Fixing plates 8 are slidably connected to the two slide rails 7. The two fixing plates 8 are fixedly connected to the corresponding measuring blocks 6 by welding. By pushing the fixing plates 8 to slide along the slide rails 7, the measuring blocks 6 can be driven to clamp the parts stably.

[0019] The functional principle of this utility model can be explained through the following operation: The six-blade high-pressure turbine of an aero-engine is placed on the base 1 with its reference surface facing upwards. The blade reference point is aligned with the first reference point positioning pins 12 on the right, upper, and rear sides of the stepped protrusion of the first positioning block 2, the first reference point positioning pins 12 on the upper part and right side of the stepped extension of the second positioning block 3, and the second reference point positioning pins 13 on the upper end of the third positioning block 4. The second locking bolt 14 on the right side of the third positioning block 4 is rotated to firmly clamp the blade, forming a precise positioning reference with three points working together. Then, the fixing plate 8 is slid along the slide rail 7 on the fixing block 5, moving the measuring block 6 to the corresponding detection position of the blade's inner diameter. After alignment, the first locking bolt 9 is passed through the threaded hole between the fixing block 5 and the measuring block 6 to lock and fix it, ensuring that the measuring hole 10 is precisely aligned with the blade detection point. Finally, the measuring instrument is inserted into the zeroing hole 11 of the measuring block 6 to complete the calibration and zeroing, eliminating measurement errors. Finally, the zeroed measuring instrument is inserted into the six measuring holes 10 on the two measuring blocks 6 in sequence to directly read the inner diameter data of the corresponding position of the blade, so as to realize the comprehensive detection of the inner diameter of the six blades. If it is necessary to measure the shaping amount, the above positioning, debugging and measurement process can be repeated before and after shaping, and the accurate shaping amount can be obtained by the difference between the two data.

[0020] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A six-piece blade inner diameter gauge for high-pressure turbines in aero-engines, characterized in that, include: The base (1) has a positioning component at its upper end. The positioning component includes a first positioning block (2), a second positioning block (3), and a third positioning block (4) fixedly connected to the upper end of the base (1). The first positioning block (2) and the second positioning block (3) are located on the left side, and the third positioning block (4) is located on the right side. The base (1) has a measuring component. The measuring component includes two fixed blocks (5) fixedly connected to the base (1). Each of the two fixed blocks (5) has a measuring block (6). Each of the two measuring blocks (6) has three measuring holes (10) and one zeroing hole (11) at its upper end. The third positioning block (4) is located between the two fixed blocks (5). The first positioning block (2) and the second positioning block (3) have multiple first reference point positioning pins (12). The upper end of the third positioning block (4) has a second reference point positioning pin (13).

2. The six-piece blade inner diameter gauge for high-pressure turbines of aero-engines according to claim 1, characterized in that: The first positioning block (2) has a rectangular groove on its rear side, and a stepped protrusion on the left side wall of the rectangular groove. The connection between the stepped protrusion and the rectangular groove is rounded. The upper end of the first positioning block (2) is a plane. Multiple first reference point positioning pins (12) are located above the first positioning block (2), to the right of the stepped protrusion, and behind the first positioning block (2), respectively.

3. The six-piece blade inner diameter gauge for high-pressure turbines of aero-engines according to claim 1, characterized in that: The second positioning block (3) has an arc-shaped groove on its left side and a stepped protrusion on its left side. Multiple first reference point positioning pins (12) are located on the right side of the stepped protrusion above the second positioning block (3).

4. The six-piece blade inner diameter gauge for high-pressure turbines of aero-engines according to claim 1, characterized in that: The third positioning block (4) is U-shaped, and the right side of the third positioning block (4) is threaded with a second locking bolt (14).

5. The six-piece blade inner diameter gauge for high-pressure turbines of aero-engines according to claim 1, characterized in that: The upper ends of the two fixing blocks (5) and the measuring block (6) are provided with threaded holes, and a first locking bolt (9) is threadedly connected to each pair of mating threaded holes.

6. The six-piece blade inner diameter gauge for high-pressure turbines of aero-engines according to claim 5, characterized in that: Each of the two fixed blocks (5) is fixedly connected to a slide rail (7) on its opposite side. Each of the two slide rails (7) is slidably connected to a fixed piece (8). The two fixed pieces (8) are fixedly connected to the corresponding measuring block (6).

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