CN216899641U - Aero-engine inlet pressure measuring device - Google Patents
Aero-engine inlet pressure measuring device Download PDFInfo
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- CN216899641U CN216899641U CN202220538610.7U CN202220538610U CN216899641U CN 216899641 U CN216899641 U CN 216899641U CN 202220538610 U CN202220538610 U CN 202220538610U CN 216899641 U CN216899641 U CN 216899641U
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Abstract
The utility model provides an inlet pressure measuring device of an aircraft engine, which comprises an air inlet, an air outlet, an airflow channel and a pressure measuring device. The air inlet is arranged on the windward side of the air inlet casing rectification support plate, the air outlet is arranged on the outer surface of the air inlet casing, one end of the air flow channel is communicated with the air inlet, the other end of the air flow channel is communicated with the air outlet, and the air flow channel is arranged in the rectification support plate. The pressure measuring device is arranged on the air outlet in a sealing mode. The air inlet is formed in the windward side of the rectifying support plate, the air outlet is formed in the outer surface of the air inlet casing, the airflow channel is arranged in the rectifying support plate to communicate the air inlet with the air outlet, so that inlet airflow can enter from the air inlet and enter into the pressure measuring device arranged at the position of the air outlet to measure pressure, the inlet pressure of the engine is measured, the air inlet pressure measuring rod head does not need to be additionally installed, the structure of the air inlet casing is simplified, and the reliability of the engine is improved.
Description
Technical Field
The utility model relates to the field of aero-engines, in particular to an aero-engine inlet pressure measuring device.
Background
In the related technical field, an aero-engine measures total pressure at an inlet of the engine by installing an inlet pressure measuring rod head on an inlet casing and connecting an inlet pressure sensor with the inlet pressure measuring rod head through a pipeline. However, in this way, an intake pressure measuring rod head needs to be added to the intake casing, and the addition of the intake pressure measuring rod head makes the structure of the intake casing more complicated, increases parts on the engine, and reduces the reliability of the engine.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an aeroengine inlet pressure measuring device, which is used for solving the technical problems that when the inlet pressure of an aeroengine is measured, an air inlet pressure measuring rod head needs to be arranged, so that parts on the engine are increased, and the reliability of the engine is reduced.
In order to achieve the purpose, the utility model adopts the technical scheme that: an aircraft engine inlet pressure measurement device is provided, the aircraft engine inlet pressure measurement device comprising:
the air inlet is arranged on the windward side of the air inlet casing rectification support plate;
the air outlet hole is formed in the outer surface of the air inlet casing;
one end of the airflow channel is communicated with the air inlet, the other end of the airflow channel is communicated with the air outlet, and the airflow channel is arranged in the rectifying support plate;
and the pressure measuring device is arranged on the air outlet hole in a sealing manner.
In one embodiment, a connecting device is arranged between the pressure measuring device and the air outlet hole.
In one embodiment, a sealing device is arranged on the surface of the pressure measuring device matched with the air outlet hole.
In one embodiment, the outlet hole is a counter-bore.
In one embodiment, a protruding portion is arranged on the windward side of the rectifying support plate, and the air inlet hole is arranged in the protruding portion.
In one embodiment, the aperture edge of the air intake aperture is a sharp edge.
In one embodiment, the air intake holes are tapered holes.
One or more technical solutions described above in the embodiments of the present invention have at least the following technical effects or advantages:
according to the aero-engine inlet pressure measuring device provided by the embodiment of the utility model, the air inlet is formed in the windward side of the rectifying support plate, the air outlet is formed in the outer surface of the air inlet casing, the airflow channel is formed in the rectifying support plate to communicate the air inlet with the air outlet, so that inlet airflow can enter from the air inlet, flows to the air outlet through the airflow channel and enters the pressure measuring device arranged at the position of the air outlet for pressure measurement, the inlet pressure of an engine is measured, an air inlet pressure measuring rod head is not required to be additionally arranged, the structure of the air inlet casing is simplified, and the reliability of the engine is improved.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft engine inlet pressure measurement device provided by an embodiment of the utility model;
FIG. 2 is a cross-sectional view taken at J-J of FIG. 1;
fig. 3 is another cross-sectional view taken at J-J of fig. 1.
Wherein the respective reference numerals are as follows:
1. an air inlet; 2. an air outlet; 3. an air flow channel; 4. a sealing device; 5. a rectification support plate.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the utility model and are not to be construed as limiting the utility model.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
The inlet pressure of the aero-engine needs to be measured, an air flow needs to be led from the front of a first-stage compressor of the aero-engine to a pressure sensor interface, most of the aero-engines at present adopt an air-bleed pipe to lead the air flow to the pressure sensor interface or design an air intake sensor to be directly installed at the inlet of the aero-engine, and considering the structural characteristics and the use requirements of the turbojet aero-engine, it is necessary to redesign an inlet pressure measurement mode to improve the quality of products. The following solutions are provided for this purpose.
Referring to fig. 1 to 3, an embodiment of the present application provides an aircraft engine inlet pressure measurement device, which includes an air inlet 1, an air outlet 2, an air flow channel 3, and a pressure measurement device (e.g., a pressure sensor, a pressure gauge, etc.). The air inlet 1 is arranged on the windward side of the air inlet casing rectification support plate 5, the air outlet 2 is arranged on the outer surface of the air inlet casing, one end of the air flow channel 3 is communicated with the air inlet 1, the other end of the air flow channel 3 is communicated with the air outlet 2, and the air flow channel 3 is arranged in the rectification support plate 5. The pressure measuring device is arranged on the air outlet hole 2 in a sealing mode. According to the aero-engine inlet pressure measuring device provided by the embodiment of the utility model, the air inlet hole 1 is formed in the windward side of the rectifying support plate 5, the air outlet hole 2 is formed in the outer surface of the air inlet casing, the airflow channel 3 is arranged in the rectifying support plate 5 to communicate the air inlet hole 1 with the air outlet hole 2, so that inlet airflow can enter from the air inlet hole 1, flows to the air outlet hole 2 through the airflow channel 3 and enters the pressure measuring device arranged at the position of the air outlet hole 2 to be measured, the inlet pressure of an engine is measured, an air inlet pressure measuring rod head is not required to be additionally arranged, the structure of the air inlet casing is simplified, and the reliability of the engine is improved.
In one embodiment, a connection device is arranged between the pressure measuring device and the air outlet hole 2. Optionally, the connecting device may be a fixed threaded sleeve, one end of the fixed threaded sleeve is matched in the air outlet 2 through threaded connection, and the other end of the fixed threaded sleeve is connected with the pressure measuring device.
In one embodiment, the surface of the pressure measuring device, which is matched with the air outlet hole 2, is provided with a sealing device 4. Optionally, sealing device 4 can be sealing washer or sealed the pad etc. through set up sealing device 4 on pressure measuring device and 2 matched with faces of venthole for the cooperation is inseparabler between pressure measuring device and the venthole 2, makes 2 positions of venthole be difficult for appearing leakage pressure, makes the pressure value that pressure measuring device surveyed more accurate.
In one embodiment, the outlet 2 is a counterbore. Through setting up venthole 2 into the counter bore for the contact surface between connecting device and the venthole 2 becomes two mutually perpendicular's face from simple one face, improves the sealed effect between venthole 2 and the connecting device.
In one embodiment, a bulge is arranged on the windward side of the rectifying support plate 5, and the air inlet hole 1 is arranged in the bulge. In one embodiment, the edges of the inlet ports 1 are sharp. Optionally, inlet port 1 is the bell mouth for it is easier to enter into in the inlet port 1 to get into the air current from the aeroengine import, and through setting up the bellying, and make inlet port 1 set up on the bellying, make inlet port 1 compare other positions of rectification extension board 5 more outstanding, make the air current pressure that enters into in the inlet port 1 be difficult for receiving the influence of rectification extension board 5, and then improve measuring accuracy.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. An aircraft engine inlet pressure measurement device, the aircraft engine inlet pressure measurement device comprising:
the air inlet is arranged on the windward side of the air inlet casing rectification support plate;
the air outlet hole is formed in the outer surface of the air inlet casing;
one end of the airflow channel is communicated with the air inlet, the other end of the airflow channel is communicated with the air outlet, and the airflow channel is arranged in the rectifying support plate;
and the pressure measuring device is arranged on the air outlet hole in a sealing manner.
2. An aircraft engine inlet pressure measuring device according to claim 1, characterised in that:
and a connecting device is arranged between the pressure measuring device and the air outlet hole.
3. An aircraft engine inlet pressure measuring device according to claim 2, characterised in that:
and a sealing device is arranged on the surface of the pressure measuring device matched with the air outlet hole.
4. An aircraft engine inlet pressure measurement device according to claim 1, characterised in that:
the air outlet is a counter bore.
5. An aircraft engine inlet pressure measuring device according to claim 1, characterised in that:
the windward side of the rectification support plate is provided with a protruding portion, and the air inlet is arranged in the protruding portion.
6. An aircraft engine inlet pressure measuring device according to claim 5, characterised in that:
the hole edge of the air inlet hole is a sharp edge.
7. An aircraft engine inlet pressure measuring device according to claim 5, characterised in that:
the air inlet hole is a conical hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220538610.7U CN216899641U (en) | 2022-03-14 | 2022-03-14 | Aero-engine inlet pressure measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220538610.7U CN216899641U (en) | 2022-03-14 | 2022-03-14 | Aero-engine inlet pressure measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216899641U true CN216899641U (en) | 2022-07-05 |
Family
ID=82189977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220538610.7U Active CN216899641U (en) | 2022-03-14 | 2022-03-14 | Aero-engine inlet pressure measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216899641U (en) |
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2022
- 2022-03-14 CN CN202220538610.7U patent/CN216899641U/en active Active
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