An aeroengine compressor rotor blade aft flow field measurement structure

Abstract

The application relates to an aero-engine compressor rotor blade rear flow field measuring structure, which comprises an outer casing with a measuring hole, an inner casing arranged in the outer casing, rotor blades and stator blades arranged between the outer casing and the inner casing, and a broken part of the outer casing and the inner casing between the rotor blades and the stator blades. An outer elongated casing and an inner elongated casing are connected between the broken parts of the outer casing, a measuring support rod is extended into the outer casing and the inner casing through the measuring hole, a measuring receiving part is arranged at one end of the measuring support rod, a displacement mechanism is connected to the outer casing and connected to the other end of the measuring support rod, the displacement mechanism can drive the measuring support rod to move in the radial direction and can drive the measuring support rod to rotate.

Description

Technical Field

[0001] This application belongs to the technical field of backflow field measurement design for aero-engine compressor rotor blades, specifically relating to a backflow field measurement structure for aero-engine compressor rotor blades. Background Technology

[0002] Between the outer and inner casings of an aero-engine compressor, the rotor blades and stator blades of each stage are distributed alternately along the axial direction. Measuring the flow field behind the rotor blades to obtain the temperature and pressure distribution in the flow field behind the rotor blades is of great significance for the design and improvement of the compressor.

[0003] In compressors, the space between adjacent rotor and stator blades is limited, making it difficult to place temperature and pressure probes behind the rotor blades to measure the flow field. Currently, the common approach is to weld multiple temperature and pressure sensors along the blade height to the leading edge of the stator blades. The test leads of these sensors are then fixed to the stator blade surface using welding clamps, extending along the blade path to measure the temperature and pressure in the flow field behind the rotor blades. Figure 1 As shown, the modified technology has the following drawbacks:

[0004] 1) To avoid interfering with the flow field, the temperature and pressure sensing elements cannot be too densely distributed in the direction of the stator blade height. Their number is limited, and they can only measure the flow field behind the rotor blades at a limited location. The difference method is required to calculate the temperature and pressure distribution of the flow field behind the rotor blades over a large range, which has a large error and is difficult to support the design and improvement of the compressor.

[0005] 2) The temperature and pressure sensing elements and their test leads are fixed to the stator blades by welding. On the one hand, the process is complicated and difficult to operate. On the other hand, it will damage the aerodynamic configuration of the stator blades and have a significant impact on the flow field behind the rotor blades, making it difficult to accurately measure the flow field behind the rotor blades. In addition, the test leads of the temperature and pressure sensing elements are subjected to strong airflow scouring on the surface of the stator blades, which poses a risk of falling off and has low reliability.

[0006] This application is made in view of the aforementioned technical deficiencies.

[0007] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent 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

[0008] The purpose of this application is to provide a flow field measurement structure behind the compressor rotor blades of an aero-engine to overcome or mitigate at least one of the known technical defects.

[0009] The technical solution of this application is:

[0010] A flow field measurement structure behind the compressor rotor blades of an aero-engine includes:

[0011] The outer casing has a measuring hole;

[0012] The inner casing is located inside the outer casing;

[0013] Rotor blades are arranged between the outer casing and the inner casing;

[0014] The stator blades are located between the outer casing and the inner casing, following the rotor blades; the outer casing and the inner casing are disconnected at the point between the rotor blades and the stator blades; the measuring hole is located between the rotor blades and the stator blades, and is located after the disconnected point on the outer casing.

[0015] An externally extended casing is connected between the disconnected parts of the external casing;

[0016] An inner extended casing is connected between the disconnected parts of the inner casing;

[0017] The measuring rod has one end extending through a measuring hole between the outer and inner housings, and a measuring sensor is installed on this end; the test lead of the measuring sensor is led out through a channel opened inside the measuring rod.

[0018] The displacement mechanism, connected to the outer casing and the other end of the measuring rod, can drive the measuring rod to move radially and rotate.

[0019] According to at least one embodiment of this application, in the above-described aero-engine compressor rotor blade backflow measurement structure, the sensing part is a temperature sensing part and a pressure sensing part.

[0020] According to at least one embodiment of this application, in the above-described aero-engine compressor rotor blade backflow field measurement structure, the lengths of the outer elongated casing and the inner elongated casing are: l lj =2.3dl y ;

[0021] Minimum distance between the rotor blade trailing edge and the measuring sensing part: l r =0.8d;

[0022] Minimum distance between the leading edge of the stator blade and the measuring sensing part: l s =0.5d;

[0023] in,

[0024] d is the diameter of the measuring rod;

[0025] l y It is the minimum distance between the trailing edge of the rotor blade and the leading edge of the stator blade.

[0026] According to at least one embodiment of this application, in the above-described aero-engine compressor rotor blade backflow field measurement structure, the displacement mechanism includes:

[0027] The motor is connected to the outer casing;

[0028] The actuator is connected between the motor and the measuring rod. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the existing aero-engine compressor rotor blade backflow field measurement structure;

[0030] Figure 2 This is a schematic diagram of the flow field measurement structure behind the compressor rotor blades of an aero-engine provided in an embodiment of this application;

[0031] Figure 3 This is a schematic diagram of the displacement mechanism provided in the embodiments of this application;

[0032] in:

[0033] 1-Outer casing; 2-Inner casing; 3-Rotor blade; 4-Stator blade; 5-Outer elongated casing; 6-Inner elongated casing; 7-Measuring support rod; 8-Displacement mechanism; 9-Motor; 10-Actuating cylinder.

[0034] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0035] 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.

[0036] 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.

[0037] 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.

[0038] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0039] A flow field measurement structure behind the compressor rotor blades of an aero-engine includes:

[0040] The outer casing 1 has a measuring hole;

[0041] Inner casing 2 is installed inside outer casing 1;

[0042] Rotor blades 3 are disposed between the outer casing 1 and the inner casing 2;

[0043] The stator blade 4 is disposed between the outer casing 1 and the inner casing 2, and is located after the rotor blade 3; the outer casing 1 and the inner casing 2 are disconnected at the part between the rotor blade 3 and the stator blade 4; the measuring hole is located between the rotor blade 3 and the stator blade 4, and is located after the disconnected part on the outer casing 1.

[0044] The outer extended casing 5 is connected between the disconnected parts of the outer casing 1;

[0045] The inner extended casing 6 is connected between the disconnected parts of the inner casing 2;

[0046] The measuring rod 7 extends through a measuring hole into the space between the outer casing 1 and the inner casing 2 at one end, and a measuring sensor is installed on this end; the test lead of the measuring sensor is led out through a channel opened inside the measuring rod 7; the measuring sensor can be a temperature sensor or a pressure sensor.

[0047] The displacement mechanism 8 is connected to the outer casing 1 and to the other end of the measuring rod 7. It can drive the measuring rod 7 to move radially and can also drive the measuring rod 7 to rotate.

[0048] Regarding the aero-engine compressor rotor blade backflow measurement structure disclosed in the above embodiments, those skilled in the art will understand that its design involves disconnecting the outer casing 1 and inner casing 2 at the points between the rotor blade 3 and stator blade 4, and connecting the outer elongated casing 5 and inner elongated casing 6 at the disconnected points. This causes the portion of the outer casing 1 and inner casing 2 after the disconnected points, as well as the stator blade 4, to be moved backward as a whole, thereby elongating the space between the rotor blade 3 and stator blade 4. This facilitates the arrangement of the measurement support rod 7 and its measuring sensing part therein, allowing for the measurement of the backflow of the rotor blade 3 without involving the modification of the stator blade 4. This avoids a significant impact on the backflow of the rotor blade 3 and has high measurement reliability.

[0049] Regarding the aero-engine compressor rotor blade backflow field measurement structure disclosed in the above embodiments, those skilled in the art will understand that it is designed with a displacement mechanism connected to the outer casing 1, which can drive the measuring support rod 7 to move radially and drive the measuring support rod 7 to rotate, that is, can drive the measuring sensing part to move radially and make the measuring sensing part swing. It can perform sweep field measurement on the backflow field of the rotor blade 3 over a large range, and can greatly reduce the interference of complex secondary flow on the backflow field of the rotor blade 3 in a limited space, accurately obtain the temperature and pressure distribution of the backflow field of the rotor blade 3, and support the design and improvement of the compressor.

[0050] In some optional embodiments, in the above-described aero-engine compressor rotor blade backflow measurement structure, the lengths of the outer elongated casing 5 and the inner elongated casing 6 are: l lj =2.3dl y Where d is the diameter of the measuring support rod 7, and l y To minimize the distance between the trailing edge of rotor blade 3 and the leading edge of stator blade 4, considering ease of operation and the impact on the flow field behind rotor blade 3, l lj It should not be too short, nor too long;

[0051] Minimum distance between the rotor blade trailing edge and the sensing part: l r =0.8d, minimum distance between the leading edge of the stator blade and the sensing part: l s =0.5d, so as to achieve efficient and accurate measurement of the flow field behind rotor blade 3.

[0052] In some optional embodiments, in the above-described aero-engine compressor rotor blade backflow measurement structure, the displacement mechanism 8 includes:

[0053] Motor 9 is connected to the outer casing 1;

[0054] The actuator 10 is connected between the motor 9 and the measuring rod 7. Specifically, the actuator 10 can drive the measuring rod 7 to move radially, and the motor 9 can drive the measuring rod 7 to rotate.

[0055] 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.

[0056] 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 structure for measuring the flow field behind the rotor blades of an aero-engine compressor, characterized in that, include: The outer casing (1) has a measuring hole; The inner casing (2) is disposed within the outer casing (1); Rotor blades (3) are disposed between the outer casing (1) and the inner casing (2); The stator blade (4) is located between the outer casing (1) and the inner casing (2), and is located after the rotor blade (3); the outer casing (1) and the inner casing (2) are disconnected at the part between the rotor blade (3) and the stator blade (4); the measuring hole is located between the rotor blade (3) and the stator blade (4), and is located after the disconnected part on the outer casing (1); The outer extended casing (5) is connected between the disconnected parts of the outer casing (1); The inner extended casing (6) is connected between the disconnected parts of the inner casing (2); The measuring rod (7) has one end inserted through a measuring hole between the outer casing (1) and the inner casing (2), and a measuring sensor is provided on this end; the test lead of the measuring sensor is led out through a channel opened inside the measuring rod (7); The displacement mechanism (8) is connected to the outer casing (1) and to the other end of the measuring rod (7). It can drive the measuring rod (7) to move radially and can drive the measuring rod (7) to rotate. The displacement mechanism (8) includes: The motor (9) is connected to the outer casing (1); The actuator (10) is connected between the motor (9) and the measuring rod (7).

2. The flow field measurement structure behind the compressor rotor blades of an aero-engine according to claim 1, characterized in that, The sensing elements are temperature sensing elements and pressure sensing elements.

3. The flow field measurement structure behind the compressor rotor blades of an aero-engine according to claim 1, characterized in that, The lengths of the outer extended casing (5) and the inner extended casing (6): ; Minimum distance between the trailing edge of rotor blade (3) and the sensing part: ; The minimum distance between the leading edge of the stator blade (4) and the sensing part is measured: ; in, To measure the diameter of the support rod (7); It is the minimum distance between the trailing edge of the rotor blade (3) and the leading edge of the stator blade (4).

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