Aero-engine intermediate pressure compressor processing casing test structure and conversion method

Abstract

The application belongs to the technical field of intermediate pressure compressor processing casing test in an aero-engine, and particularly relates to an aero-engine intermediate pressure compressor processing casing test structure and a changing method, which is provided with a rear casing behind an outer casing, is used for assembling with a stator inner ring and stator blades, and is designed as a horizontal split casing, so as to facilitate the assembly of the structure. In addition, when different types of processing casings need to be changed in the test, the processing casing can be replaced half by half on the test bench under the condition of ensuring the overall connection of the structure, which is convenient and fast.

Description

Technical Field

[0001] This application belongs to the field of test technology for intermediate compressor treatment casing in aero-engines, specifically relating to a test structure and replacement method for intermediate compressor treatment casing in aero-engines. Background Technology

[0002] To improve the surge margin of the compressor in aero-engines, a treatment casing technology is adopted. The treatment casing is set inside the casing outside the rotor blades, and a treatment cavity is formed between the treatment casing and the casing outside the rotor blades. The treatment casing has a pre-treatment slot and a post-treatment slot that communicate with the treatment cavity. By using the pressure difference, the airflow at the rotor blade tip is continuously drawn away from the main flow channel and forms a return flow through the post-treatment slot, the treatment cavity, and the pre-treatment cavity. This reduces the flow resistance of the main flow channel, delays stall flutter, and improves the flutter margin.

[0003] Currently, corresponding test structures have been designed to verify the performance of different types of processing casings, such as... Figure 1 As shown, it includes:

[0004] The front casing is a full-ring casing;

[0005] The outer casing is a horizontally split casing with multiple upper journal mounting holes; the two halves of the outer casing are connected by bolts through a connecting edge;

[0006] The processing casing is installed inside the outer casing. Its front end is bolted to the front end of the front casing and the front end of the outer casing via connecting edges. It is centered with the front casing and the outer casing via a stop.

[0007] The rotor disc is installed inside the processing casing;

[0008] Multiple rotor blades, with the blade roots connected circumferentially to the outer edge of the rotor disk and the blade tips pointing towards the processing casing;

[0009] The rotor shaft has a front journal connected to the rear side of the rotor disc and a rear end extending out of the rear end of the outer casing, which is connected to the power drive mechanism, specifically a drive motor, so that it can drive each rotor blade to rotate through the rotor disc.

[0010] The stator inner ring is fitted around the outer circumference of the rotor shaft and is located behind the rotor disc. It is made of two sections connected by bolts, with a lower journal mounting hole formed in between.

[0011] Multiple adjustable stator blades are arranged circumferentially between the outer casing and the inner ring of the stator. The lower journal is inserted into the mounting holes of each lower journal, and the upper journal extends out from the mounting holes of each upper journal and is connected to the angle adjustment mechanism. Each adjustable stator blade can rotate synchronously under the drive of the angle adjustment mechanism.

[0012] In the current test structure of the compressor treatment casing in aero-engines, the highest point of the front end of each rotor blade tip is radially higher than the lowest point of the rear end of the treatment casing. In actual assembly, it is not possible to assemble each rotor blade with the outer casing first and then remove the treatment casing from the front end. Instead, each rotor blade must be fixed to the treatment casing with special tooling before assembling the outer casing. When a different type of treatment casing needs to be replaced during testing, the test structure must be disassembled from the test bench, transported to the assembly workshop, disassembled first the outer casing, then disassembled the treatment casing backwards, and then assembled and replaced with the new treatment casing according to the above assembly process, transported and installed on the test bench. The whole process is cumbersome, cannot be directly replaced on the test bench, is time-consuming, labor-intensive, inefficient, and has a long cycle.

[0013] This application is made in view of the aforementioned technical deficiencies.

[0014] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0015] The purpose of this application is to provide a test structure and replacement method for the compressor handling casing in an aero-engine, so as to overcome or mitigate at least one of the known technical defects.

[0016] The technical solution of this application is:

[0017] One aspect provides a test structure for the compressor handling casing in an aero-engine, including:

[0018] The front casing is a full-ring casing;

[0019] The outer casing is a horizontally split casing, with the two halves of the outer casing connected by bolts via a connecting edge;

[0020] The processing casing is a horizontally split casing, which is installed inside the outer casing. Its front end is connected to the front end of the front casing and the front end of the outer casing by bolts through a connecting edge.

[0021] The rotor disc is installed inside the processing casing;

[0022] Multiple rotor blades, with the blade roots connected circumferentially to the outer edge of the rotor disk and the blade tips pointing towards the processing casing;

[0023] The rotor shaft has a front journal connected to the rear side of the rotor disc and a rear end extending out of the rear end of the outer casing.

[0024] The rear casing has multiple upper journal mounting holes, and its front end is bolted to the rear end of the outer casing via a connecting edge.

[0025] The stator inner ring is fitted around the outer circumference of the rotor shaft and is installed inside the rear casing. It has multiple lower journal mounting holes.

[0026] Multiple adjustable stator blades are arranged circumferentially between the rear casing and the inner ring of the stator. The lower journals are inserted into the mounting holes of each lower journal, and the upper journals extend out from the mounting holes of each upper journal.

[0027] According to at least one embodiment of this application, in the above-described test structure for the compressor handling casing of an aero-engine, the front casing, the outer casing, and the handling casing are centered by a stop.

[0028] The outer casing and the rear casing are centered using a stop.

[0029] According to at least one embodiment of this application, in the above-described test structure for the compressor handling casing of an aero-engine, the rear casing is a horizontally split casing; the two halves of the rear casing are connected by bolts through a connecting edge.

[0030] The stator inner ring is made up of two sections connected by bolts, with mounting holes for each lower journal formed between the two sections.

[0031] On the other hand, a method for assembling a test structure for a compressor handling casing in an aero-engine is provided, for assembling the aforementioned test structure for a compressor handling casing in an aero-engine, including:

[0032] Assemble the rotor disk, rotor blades, and rotor shaft;

[0033] Assemble the rear casing, stator inner ring, and adjustable stator blades;

[0034] The rotor blades are fixed to the processor casing using specialized tooling;

[0035] The two halves of the outer casing are bolted together and assembled onto the outer periphery of the processing casing.

[0036] The rear end of the front casing, the front end of the outer casing, and the front connecting edge of the processing casing are bolted together.

[0037] The rear end of the outer casing and the front end of the rear casing are connected by bolts.

[0038] Another aspect provides a method for replacing the test structure of the compressor treatment casing in an aero-engine, which enables the replacement of different models of the compressor treatment casing in the aforementioned test structure of the aero-engine during testing, including:

[0039] Remove the bolts connecting the two halves of the outer casing;

[0040] Remove the bolts connecting the front end of one half of the outer casing to the front end of the corresponding half of the processing casing and the rear end of the front casing, and remove the bolts connecting the rear end of the half of the outer casing to the front end of the rear casing. Then, remove the half of the outer casing and the corresponding half of the processing casing, replace the corresponding half of the processing casing, and connect the front end of the half of the outer casing to the front end of the replacement half of the processing casing and the rear end of the front casing with bolts, and connect the rear end of the half of the outer casing to the front end of the rear casing with bolts.

[0041] Remove the bolts connecting the front end of the other half of the outer casing to the front end of the corresponding half of the processing casing and the rear end of the front casing, and remove the bolts connecting the rear end of the half of the outer casing to the front end of the rear casing. Then, remove the half of the outer casing and the corresponding half of the processing casing, replace the corresponding half of the processing casing, and connect the front end of the half of the outer casing to the front end of the replacement half of the processing casing and the rear end of the front casing with bolts, and connect the rear end of the half of the outer casing to the front end of the rear casing with bolts. Attached Figure Description

[0042] Figure 1 This is a schematic diagram of the test structure of the compressor handling casing in an aero-engine provided in the embodiments of this application;

[0043] Figure 2 yes Figure 1 Sectional view along axis AA;

[0044] in:

[0045] 1-Front casing; 2-Outer casing; 3-Processing casing; 4-Rotor disc; 5-Rotor blade; 6-Rotor shaft; 7-Rear casing; 8-Stator inner ring; 9-Adjustable stator blade.

[0046] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0047] 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.

[0048] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0049] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection 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 an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0050] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0051] One aspect provides a test structure for the compressor handling casing in an aero-engine, including:

[0052] Front casing 1 is a full-ring casing;

[0053] The outer casing 2 is a horizontally split casing, and the two halves of the outer casing 2 are connected by bolts through a connecting edge;

[0054] The processing casing 3 is a horizontally split casing, which is installed inside the outer casing 2. Its front end is connected to the front end of the front casing 1 and the front end of the outer casing 2 by bolts through connecting edges. Alternatively, the processing casing 3 can be designed to be connected to each other by bolts through connecting edges, and the same set of bolts is used between the connecting edges of the two halves of the outer casing 2.

[0055] Rotor disk 4 is installed inside the processing casing 3;

[0056] Multiple rotor blades 5, with the blade roots connected circumferentially to the outer edge of the rotor disk and the blade tips pointing towards the processing casing 3;

[0057] The rotor shaft 6 has a front journal connected to the rear side of the rotor disc 4, and the rear end extends out of the rear end of the outer casing 3.

[0058] The rear casing 7 has multiple upper journal mounting holes, and its front end is bolted to the rear end of the outer casing 2 via a connecting edge.

[0059] The stator inner ring 8 is sleeved on the outer circumference of the rotor shaft 6 and is installed inside the rear casing 7. It has multiple lower shaft journal mounting holes.

[0060] Multiple adjustable stator blades 9 are arranged circumferentially between the rear casing 7 and the stator inner ring 8. The lower journals are inserted into the mounting holes of each lower journal, and the upper journals extend out from the mounting holes of each upper journal.

[0061] In some optional embodiments, in the above-described test structure of the compressor handling casing in an aero-engine, the front casing 1, the outer casing 2, and the handling casing 3 are centered by means of a stop, and the outer casing 2 and the rear casing 7 are centered by means of a stop, so that the positioning between the components is reliable.

[0062] In some optional embodiments, in the above-described test structure of the compressor handling casing in an aero-engine, the rear casing 7 is a horizontally split casing; the two halves of the rear casing 7 are connected by bolts through a connecting edge;

[0063] The stator inner ring 8 is made of two sections connected by bolts, with mounting holes for each lower journal formed between the two sections for easy assembly.

[0064] On the other hand, a method for assembling a test structure for a compressor handling casing in an aero-engine is provided, for assembling the aforementioned test structure for a compressor handling casing in an aero-engine, including:

[0065] The rotor disk 4, rotor blades 5, and rotor shaft 6 are assembled. The specific process can be referred to the existing assembly process of rotor disk 4, rotor blades 5, and rotor shaft 6, and will not be described in more detail here.

[0066] The rear casing 7, stator inner ring 8, and adjustable stator blades 9 are assembled. The specific process can refer to the existing assembly process of the rear casing 7, stator inner ring 8, and adjustable stator blades 9. No further detailed explanation will be given here.

[0067] The rotor blades 5 are fixed to the processing casing 3 using special tooling;

[0068] The two halves of the outer casing 2 are connected by bolts and assembled to the outer periphery of the processing casing 3. The specific process can be referred to the existing assembly process of the outer casing 2, processing casing 3, and rotor blades 5, and will not be explained in more detail here.

[0069] The rear end of the front casing 1, the front end of the outer casing 2, and the front connecting edge of the processing casing 3 are connected by bolts.

[0070] The rear end of the outer casing 2 and the front end of the rear casing 7 are connected by bolts.

[0071] Another aspect provides a method for replacing the test structure of the compressor treatment casing in an aero-engine, which enables the replacement of different models of the compressor treatment casing in the aforementioned test structure of the aero-engine during testing, including:

[0072] Remove the bolts connecting the two halves of the outer casing 2;

[0073] Remove the bolts connecting the front end of half of the outer casing 2 to the front end of the corresponding half of the processing casing 3 and the rear end of the front casing 1, and remove the bolts connecting the rear end of the half of the outer casing 2 to the front end of the rear casing 7. Then remove the half of the outer casing 2 and the corresponding half of the processing casing 3, replace the corresponding half of the processing casing, and connect the front end of the half of the outer casing 2 to the front end of the replacement half of the processing casing 3 and the rear end of the front casing 1 with bolts, and connect the rear end of the half of the outer casing 2 to the front end of the rear casing 7 with bolts.

[0074] Remove the bolts connecting the front end of the other half of the outer casing 2 to the front end of the corresponding half of the processing casing 3 and the rear end of the front casing 1, and remove the bolts connecting the rear end of the half of the outer casing 2 to the front end of the rear casing 7. Then, remove the half of the outer casing 2 and the corresponding half of the processing casing 3, and replace the corresponding half of the processing casing. Connect the front end of the half of the outer casing 2 to the front end of the replacement half of the processing casing 3 and the rear end of the front casing 1 with bolts, and connect the rear end of the half of the outer casing 2 to the front end of the rear casing 7 with bolts.

[0075] Regarding the test structure of the compressor handling casing of an aero-engine disclosed in the above embodiments, those skilled in the art will understand that a rear casing 7 is provided after the outer casing 2 for assembly with the stator inner ring 8 and its stator blades 8, and the handling casing 3 is designed as a horizontally split casing to facilitate the assembly of the structure. The assembly process can be referred to the assembly method of the test structure of the compressor handling casing of an aero-engine disclosed above. In addition, when it is necessary to replace different models of handling casing 3 during the test, the handling casing 3 can be replaced half by half on the test bench while ensuring the overall connection of the structure. This is convenient and quick. The specific process can be referred to the replacement method of the test structure of the compressor handling casing of an aero-engine disclosed above.

[0076] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0077] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for replacing the test structure of the compressor treatment casing in an aero-engine, characterized in that, The test structure for the compressor handling casing in an aero-engine includes: The front casing (1) is a ring casing; The outer casing (2) is a horizontally split casing, and the two halves of the outer casing (2) are connected by bolts through the connecting edge; The processing casing (3) is a horizontal split casing, which is installed inside the outer casing (2). Its front end is connected to the front end of the front casing (1) and the front end of the outer casing (2) by bolts through the connecting edge. Rotor disc (4) is installed inside the processing casing (3); Multiple rotor blades (5) have their root parts connected circumferentially to the outer edge of the rotor disk, and their tips pointing towards the processing casing (3). The rotor shaft (6) has its front end journal connected to the rear side of the rotor disc (4), and its rear end extends out of the rear end of the outer casing (2); The rear casing (7) has multiple upper journal mounting holes and is bolted to the rear end of the outer casing (2) via a connecting edge. The stator inner ring (8) is sleeved on the outer circumference of the rotor shaft (6) and is installed inside the rear casing (7), and has multiple lower journal mounting holes; Multiple adjustable stator blades (9) are arranged circumferentially between the rear casing (7) and the stator inner ring (8). The lower journal is inserted into each lower journal mounting hole, and the upper journal extends out from each upper journal mounting hole. Assembly method for the test structure of the compressor treatment casing in an aero-engine, including: Assemble the rotor disk (4), rotor blades (5), and rotor shaft (6); Assemble the rear casing (7), stator inner ring (8), and adjustable stator blades (9); The rotor blades (5) are fixed to the processing casing (3) using special tooling; The two halves of the outer casing (2) are bolted together and assembled onto the outer periphery of the processing casing (3); The front casing (1) rear end, the outer casing (2) front end, and the processing casing (3) front end are connected by bolts. The rear end of the outer casing (2) and the front end of the rear casing (7) are connected by bolts; The test structure replacement method for the compressor treatment casing in an aero-engine includes: Remove the bolts connecting the two halves of the outer casing (2); Remove the bolts connecting the front end of half of the outer casing (2) to the front end of the corresponding half of the processing casing (3) and the rear end of the front casing (1), and remove the bolts connecting the rear end of the half of the outer casing (2) to the front end of the rear casing (7), and then remove the half of the outer casing (2) and the corresponding half of the processing casing (3), replace the corresponding half of the processing casing, and connect the front end of the half of the outer casing (2) to the front end of the replacement half of the processing casing (3) and the rear end of the front casing (1) with bolts, and connect the rear end of the half of the outer casing (2) to the front end of the rear casing (7) with bolts. Remove the bolts connecting the front end of the other half of the outer casing (2) to the front end of the corresponding half of the processing casing (3) and the rear end of the front casing (1), and remove the bolts connecting the rear end of the half of the outer casing (2) to the front end of the rear casing (7), and then remove the half of the outer casing (2) and the corresponding half of the processing casing (3), replace the corresponding half of the processing casing, connect the front end of the half of the outer casing (2) to the front end of the replacement half of the processing casing (3) and the rear end of the front casing (1) with bolts, and connect the rear end of the half of the outer casing (2) to the front end of the rear casing (7) with bolts.

2. The method for replacing the test structure of the compressor treatment casing in an aero-engine according to claim 1, characterized in that, In the test structure of the compressor handling casing in an aero-engine, the front casing (1), the outer casing (2), and the handling casing (3) are centered by a stop; The outer casing (2) and the rear casing (7) are centered by means of a stop.

3. The method for replacing the test structure of the compressor treatment casing in an aero-engine according to claim 1, characterized in that, In the test structure of the compressor handling casing in the aero-engine, the rear casing (7) is a horizontal split casing; the two halves of the rear casing (7) are connected by bolts through the connecting edge; The inner ring (8) of the stator is made of two sections connected by bolts, and each section forms a mounting hole for the lower journal.

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