CN114441089A - Total pressure measurement rake and method for measuring total pressure in flow channel of aircraft engine - Google Patents
Total pressure measurement rake and method for measuring total pressure in flow channel of aircraft engine Download PDFInfo
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- CN114441089A CN114441089A CN202210101507.0A CN202210101507A CN114441089A CN 114441089 A CN114441089 A CN 114441089A CN 202210101507 A CN202210101507 A CN 202210101507A CN 114441089 A CN114441089 A CN 114441089A
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- 238000009530 blood pressure measurement Methods 0.000 title claims abstract description 43
- 238000000034 method Methods 0.000 title claims abstract description 13
- 229910052751 metal Inorganic materials 0.000 claims abstract description 16
- 239000002184 metal Substances 0.000 claims abstract description 16
- 238000004891 communication Methods 0.000 claims abstract description 14
- XFWJKVMFIVXPKK-UHFFFAOYSA-N calcium;oxido(oxo)alumane Chemical compound [Ca+2].[O-][Al]=O.[O-][Al]=O XFWJKVMFIVXPKK-UHFFFAOYSA-N 0.000 claims description 4
- 239000004568 cement Substances 0.000 claims description 4
- 238000005259 measurement Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/0007—Fluidic connecting means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The application relates to a total pressure measurement harrow includes: the cross section of the inner wall of the sleeve is of a special-shaped structure, and the outer wall of one end of the sleeve is provided with an annular connecting edge; one end of the inner branch pipe extends into the other end of the sleeve, and the outer wall of the inner branch pipe is at least partially attached to the inner wall of the sleeve; one side of the adapter ring is connected with the annular connecting edge, and the other side of the adapter ring is provided with an adapter edge; one end of the outer branch pipe extends into the sleeve pipe from the end, back to the inner branch pipe, of the sleeve pipe, and the end of the outer branch pipe is connected with one end, extending into the sleeve pipe, of the inner branch pipe in a threaded fit mode; the clamp is connected with the switching edge and clamps the outer branch pipe; the total pressure measuring head is connected with the other end of the inner branch pipe, is provided with a communicating hole and a plurality of total pressure measuring holes; and one end of each thin-wall metal gas-guiding pipe extends into the other end of the outer support pipe, penetrates through the inner branch pipe and the communication hole, is connected to the total pressure measuring head and is correspondingly communicated with a total pressure measuring hole. In addition, the invention relates to an aeroengine flow passage internal total pressure measurement method implemented based on the total pressure measurement rake.
Description
Technical Field
The application belongs to the technical field of total pressure measurement in an aircraft engine flow passage, and particularly relates to a total pressure measurement rake and a total pressure measurement method in the aircraft engine flow passage.
Background
The total pressure in the flow passage of the aero-engine is one of important aerodynamic parameters of the engine, the total pressure in the flow passage of the engine is accurately measured, and the method has important significance for design and improvement of the aero-engine.
Currently, the total pressure in the flow channel is mostly measured by externally inserting and fixing a total pressure measuring rake on a casing of the aeroengine, as shown in fig. 1, the technical scheme has the following defects:
1) the measuring end of the total pressure measuring rake is formed by welding and surfacing a plurality of thin-wall metal air guide pipes, is low in strength, easy to bend and even break, small in insensitive angle to air flow, mostly located in a range of-15 degrees to 15 degrees, and difficult to ensure the reliability of a total pressure measuring result when the included angle between the measuring end and the air flow in an aircraft engine flow channel exceeds the range, and in addition, the thin-wall metal air guide pipes cannot be welded by argon arc welding and are not applicable when the temperature of the air flow in the aircraft engine flow channel exceeds 800 ℃;
2) the total pressure measurement rake is fixed on the aeroengine casing in an external insertion mode, the distribution range of measurement points at the measurement end of the total pressure measurement rake is limited by the size of an opening on the aeroengine casing, if the distribution range of the measurement points is desired to be enlarged, the size of the opening on the aeroengine casing needs to be enlarged, and the size of the opening on the aeroengine casing is too large, so that the strength and the rigidity of the aeroengine casing are weakened, and reliable sealing is difficult to realize;
3) the total pressure measurement rake is adopted to be nonadjustable in the radial position in the channel of the aeroengine, in order to realize the measurement of the total pressure of each radial position in the channel of the aeroengine, a plurality of total pressure measurement rakes with different lengths are arranged in the circumferential direction of the aeroengine, and the total pressure measurement rakes with more number can increase the blocking effect of airflow in the aeroengine, so that the local flow field is seriously distorted, the airflow flow in the channel of the aeroengine is influenced, and the accurate measurement of the total pressure in the aeroengine is difficult to realize.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The purpose of the present application is to provide a total pressure measurement rake and a total pressure measurement method in a flow passage of an aircraft engine, so as to overcome or alleviate technical defects of at least one known aspect.
The technical scheme of the application is as follows:
one aspect provides a total pressure measurement rake, comprising:
the cross section of the inner wall of the sleeve is of a special-shaped structure, and the outer wall of one end of the sleeve is provided with an annular connecting edge;
one end of the inner branch pipe extends into the other end of the sleeve, and the outer wall of the inner branch pipe is at least partially attached to the inner wall of the sleeve;
one side of the adapter ring is connected with the annular connecting edge, and the other side of the adapter ring is provided with an adapter edge;
one end of the outer branch pipe extends into the sleeve pipe from the end, back to the inner branch pipe, of the sleeve pipe, and the end of the outer branch pipe is connected with one end, extending into the sleeve pipe, of the inner branch pipe in a threaded fit mode;
the clamp is connected with the switching edge and clamps the outer branch pipe;
the total pressure measuring head is connected with the other end of the inner branch pipe, is provided with a communicating hole and a plurality of total pressure measuring holes; the communicating hole is communicated with the inside of the inner support pipe and each total pressure measuring hole; each total pressure measuring hole is distributed in an arc shape;
and one end of each thin-wall metal gas-guiding pipe extends into the outer branch pipe from the other end of the outer branch pipe, penetrates through the inner branch pipe, extends into the communication hole, is connected to the total pressure measuring head and is correspondingly communicated with a total pressure measuring hole.
According to at least one embodiment of the present application, in the total pressure measuring rake, there are two transition edges distributed on both sides of the casing.
According to at least one embodiment of the application, in the total pressure measuring rake, the outer wall of the outer support pipe is provided with a plurality of annular clamping grooves; each annular clamping groove is axially distributed along the outer support pipe;
the clamp hoop is clamped in an annular clamping groove.
According to at least one embodiment of the present application, in the total pressure measuring rake, the space between the communication hole and each total pressure measuring hole is filled with pure calcium aluminate high-temperature cement.
According to at least one embodiment of the present application, in the total pressure measuring rake, the total pressure measuring head includes:
one side of the arc-shaped plate is connected with one end of the inner support pipe, which is back to the sleeve pipe, and the side is provided with a communication hole;
the total pressure measuring holes are distributed on one arc edge of the arc-shaped plate.
According to at least one embodiment of the present application, in the total pressure measuring rake, the total pressure measuring head further includes:
the connecting plate is connected to one side of the arc-shaped plate, which is back to the inner branch pipe, and a communicating cavity is formed between the connecting plate and the inner branch pipe; the communicating cavity is communicated with the communicating hole and each total pressure measuring hole.
According to at least one embodiment of the present application, the total pressure measuring rake further includes:
the plurality of fairing is connected to the total pressure measuring head, each fairing correspondingly covers one total pressure measuring hole, the front end of each fairing is provided with an air inlet communicated with the corresponding total pressure measuring hole, and the side wall of each fairing is provided with a plurality of exhaust holes distributed along the circumferential direction.
According to at least one embodiment of the present application, in the total pressure measuring rake, each air inlet hole has a windward angle of 90 °.
In another aspect, a method for measuring total pressure in a flow passage of an aircraft engine is provided, which includes:
the sleeve extends into an aircraft engine flow channel from the outer side of an aircraft engine casing through an opening on the aircraft engine casing, and an annular connecting edge on the sleeve is connected to the outer side of the aircraft engine casing;
extending the inner branch pipe into the sleeve from the flow passage of the aircraft engine;
extending the outer branch pipe into the sleeve from the outer side of the aeroengine casing, and connecting the outer branch pipe with the inner branch pipe in a threaded fit manner;
the outer branch pipe is hooped by a hoop;
wherein,
the adapter ring is connected to the connecting edge;
the clamp is connected to the switching edge;
the total pressure measuring head is connected to the inner branch pipe;
each thin-wall metal gas-leading pipe is connected to the total pressure measuring head and is led out through the inner branch pipe and the outer branch pipe;
when the clamp is loosened, the radial position of the total pressure measuring head in the flow channel of the aircraft engine can be adjusted by pushing and pulling the outer support pipe from the outer side of the casing of the aircraft engine, and after the total pressure measuring head is adjusted in place, the outer support pipe is clamped by the clamp again, so that the total pressure measurement of each radial position in the flow channel of the aircraft engine can be realized.
Drawings
FIG. 1 is a schematic diagram of a prior art total pressure measurement rake for measuring total pressure in an aircraft engine flowpath;
FIG. 2 is a schematic diagram of a total pressure measurement rake provided by an embodiment of the present application;
FIG. 3 is a sectional view taken along line A-A of FIG. 2;
FIG. 4 is a partial schematic view of a total pressure measurement rake provided by an embodiment of the present application;
FIG. 5 is a sectional view taken along line B-B of FIG. 4;
FIG. 6 is a schematic diagram of a total pressure measurement rake provided by an embodiment of the application for measuring total pressure in a flow passage of an aircraft engine;
wherein:
1-a sleeve; 2-inner branch pipe; 3-a transfer ring; 4-outer branch pipe; 5, clamping a hoop; 6-total pressure measuring head; 7-thin-walled metal bleed pipes; 8-arc-shaped plates; 9-a connecting plate; 10-a fairing; 11-aeroengine case.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; in addition, the drawings are used for illustrative purposes, and the positional relationship is only for illustrative purposes and is not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and the like as used in the description of the present application are to be construed broadly, e.g., the connection may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 6.
One aspect provides a total pressure measurement rake, comprising:
the cross section of the inner wall of the sleeve 1 is of a special-shaped structure, and the outer wall of one end of the sleeve is provided with an annular connecting edge;
one end of the inner branch pipe 2 extends into the other end of the sleeve 1, and the outer wall of the inner branch pipe is at least partially attached to the inner wall of the sleeve 1;
one side of the adapter ring 3 is connected with the annular connecting edge, and the other side of the adapter ring is provided with an adapter edge;
one end of the outer branch pipe 4 extends into the sleeve 1 from the end back to the inner branch pipe 2, and the end is connected with one end of the inner branch pipe 2 extending into the sleeve 1 in a threaded fit manner;
the hoop 5 is connected with the switching edge and hoops the outer branch pipe 4;
the total pressure measuring head 6 is connected to the other end of the inner branch pipe 2, is provided with a communication hole and a plurality of total pressure measuring holes; the communicating hole is communicated with the interior of the inner branch pipe 2 and each total pressure measuring hole; each total pressure measuring hole is distributed in an arc shape;
and one end of each thin-wall metal gas guide pipe 7 extends into the outer branch pipe 4 from the other end of the outer branch pipe, penetrates through the inner branch pipe 2, extends into the communication hole, is connected to the total pressure measuring head 5 and is correspondingly communicated with a total pressure measuring hole.
With the total pressure measurement rake disclosed by the embodiment, the measurement of the total pressure in the flow passage of the aircraft engine can be carried out by referring to the following steps:
the sleeve 1 extends into an aircraft engine flow channel from the outer side of an aircraft engine casing 11 through an opening on the aircraft engine casing 11, and an annular connecting edge on the sleeve is connected to the outer side of the aircraft engine casing 11;
extending the inner branch pipe 2 into the sleeve 1 from the flow passage of the aircraft engine;
the outer support pipe 4 extends into the sleeve 1 from the outer side of the aeroengine casing 11 and is in threaded fit connection with the inner support pipe 2;
wherein,
the adapter ring 3 is connected to the connecting edge and can be connected to the aircraft engine case 11 through a bolt together with the connecting edge;
the clamp 5 is connected to the switching edge, and can be connected through a bolt specifically;
the total pressure measuring head 6 is connected to the inner branch pipe 2;
each thin-wall metal gas-leading pipe 7 is connected with a total pressure measuring head 6 and is led out through an inner branch pipe 2 and an outer branch pipe 4;
the outer branch pipe 4 is hooped by a hoop 5, and the total pressure in the flow passage of the aircraft engine is measured.
For the total pressure measurement rake disclosed in the above embodiment, it can be understood by those skilled in the art that when the total pressure measurement rake is used to measure the total pressure in the aircraft engine flow passage, the inner branch pipe 2 can be installed from the aircraft engine flow passage, specifically, the inner branch pipe 2 can be installed from the inlet or the outlet of the aircraft engine flow passage, the outer branch pipe 4 can be installed from the outer side of the aircraft engine casing 11, and the total pressure in the aircraft engine flow passage is measured after being connected with the inner branch pipe 2, so that the measurement points at the measurement end of the total pressure measurement rake can be distributed in a large range without enlarging the size of the opening in the aircraft engine casing.
For the total pressure measuring rake disclosed in the above embodiment, it can be further understood by those skilled in the art that the cross section of the inner wall of the casing 1 is designed to be of a special-shaped structure, specifically, a rectangular, oval or carrying pole shape, and after the inner branch pipe 2 is inserted into the inner branch pipe, the inner branch pipe 2 can be effectively prevented from rotating in the circumferential direction, so that the inner branch pipe 2 is positioned in the circumferential direction, and the outer branch pipe 3 is conveniently connected with the inner branch pipe 2 after extending into the casing 1.
With respect to the total pressure measurement rake disclosed in the above embodiments, it will also be appreciated by those skilled in the art that, when the total pressure in the flow passage of the aircraft engine is measured, the pressure in the flow passage can be measured by loosening the clamp 5, from the outside of the aircraft engine casing 11, the radial position of the total pressure measuring head 6 in the flow channel of the aeroengine is adjusted in a mode of pushing and pulling the outer branch pipe 4, after the total pressure measuring head is adjusted in place, the outer branch pipe 4 is hooped again by the hoop 5, the method can realize total pressure measurement of radial positions in the aircraft engine flow channel, is convenient and quick, and can not obviously increase the blocking effect of airflow in the aircraft engine flow channel and ensure the accuracy of total pressure measurement in the aircraft engine flow channel compared with the current mode of measuring the total pressure of radial positions in the aircraft engine flow channel by arranging a plurality of total pressure measurement rakes with different lengths in the circumferential direction of the aircraft engine.
For the total pressure measuring rake disclosed in the above embodiment, it can be understood by those skilled in the art that one end of each thin-wall metal bleed pipe 7 is designed to extend into the other end of the outer branch pipe 4, penetrate through the inner branch pipe 2, extend into the communication hole, be connected to the total pressure measuring head 5, and be communicated with the corresponding total pressure measuring hole, and the measuring end is located inside the total pressure measuring head 6 and protected by the total pressure measuring head 6, so that the total pressure measuring rake is not easy to bend and break.
In some alternative embodiments, two adapting edges are arranged on the total pressure measuring rake and distributed on two sides of the casing 1.
In some optional embodiments, in the total pressure measuring rake, the outer wall of the outer support pipe 4 is provided with a plurality of annular clamping grooves; each annular clamping groove is distributed along the axial direction of the outer support pipe 4;
the hoop 5 is hooped in one annular clamping groove and limited by the annular clamping groove, the positioning effect of the outer branch pipe 4 can be guaranteed, and the hoop can be hooped in the annular clamping groove at the response position when the total pressure at different radial positions in the flow channel of the aircraft engine is measured.
In some optional embodiments, in the total pressure measuring rake, the space between the communication hole and each total pressure measuring hole is filled with pure calcium aluminate high-temperature cement so as to position and fix each thin-wall metal air-guiding pipe 7, protect each thin-wall metal air-guiding pipe 7 from bending and breaking, protect each thin-wall metal air-guiding pipe 7 from high temperature, measure the total pressure in the aircraft engine flow passage at a higher temperature, and measure the total pressure in the aircraft engine flow passage effectively within 1000 ℃.
In some alternative embodiments, in the total pressure measuring rake, total pressure measuring head 6 includes:
an arc-shaped plate 8, one side of which is connected with one end of the inner supporting pipe 2 back to the sleeve 1 and is provided with a communication hole;
the total pressure measuring holes are distributed on one arc edge of the arc plate 8.
In some optional embodiments, in the total pressure measuring rake, the total pressure measuring head 6 further includes:
the connecting plate 9 is connected to one side, back to the inner branch pipe 2, of the arc-shaped plate 8, and a communicating cavity is formed between the connecting plate and the inner branch pipe 2; the communicating cavity is communicated with the communicating holes and all the total pressure measuring holes, and pure calcium aluminate high-temperature cement is filled in the communicating cavity.
For the total pressure measuring rake disclosed in the above embodiments, it can be understood by those skilled in the art that the total pressure measuring head 6 is composed of the arc-shaped plate 8 and the connecting plate 9 which are connected with each other, and can be conveniently disassembled and assembled, and the assembling is easy.
In some optional embodiments, the total pressure measuring rake further includes:
a plurality of cowlings 10 connect and to total pressure measuring head 6 on, and every cowling 10 corresponds and covers a total pressure measuring hole, and its front end has and corresponds the inlet port of total pressure measuring hole intercommunication, and the lateral wall has a plurality of exhaust holes along circumference distribution.
For the total pressure measuring rake disclosed in the above embodiments, it can be understood by those skilled in the art that the total pressure measuring rake is designed to connect the fairing 10 to the total pressure measuring head 6 to cover the corresponding total pressure measuring hole, so that the range of the insensitive angle of the total pressure measuring rake to the air flow can be enlarged to-25 degrees to 25 degrees, and the accurate measurement of the total pressure in the flow channel of the aircraft engine can be realized in a larger sensitive angle range.
In some optional embodiments, in the total pressure measuring rake, the windward angle of each air inlet hole is 90 °.
In another aspect, a method for measuring total pressure in a flow passage of an aircraft engine is provided, which includes:
the sleeve 1 extends into an aircraft engine flow channel from the outer side of an aircraft engine casing 11 through an opening on the aircraft engine casing 11, and an annular connecting edge on the sleeve is connected to the outer side of the aircraft engine casing 11;
extending the inner branch pipe 2 into the sleeve 1 from the flow passage of the aircraft engine;
the outer support pipe 4 extends into the sleeve 1 from the outer side of the aeroengine casing 11 and is in threaded fit connection with the inner support pipe 2;
the outer branch pipe 4 is hooped by a hoop 5;
wherein,
the adapter ring 3 is connected to the connecting edge;
the clamp 5 is connected to the switching edge;
the total pressure measuring head 6 is connected to the inner branch pipe 2;
each thin-wall metal gas-guiding pipe 7 is connected to a total pressure measuring head 6 and is led out through an inner branch pipe 2 and an outer branch pipe 4;
when the clamp 5 is loosened, the radial position of the total pressure measuring head 6 in the aircraft engine flow passage can be adjusted by pushing and pulling the outer branch pipe 4 from the outer side of the aircraft engine casing 11, and after the total pressure measuring head is adjusted in place, the clamp 5 is used for clamping the outer branch pipe 4 again, so that the total pressure measurement of each radial position in the aircraft engine flow passage can be realized.
For the method for measuring total pressure in the flow passage of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the method is implemented based on the total pressure measurement rake disclosed in the above embodiment, specific relevant points may refer to the description of relevant parts of the total pressure measurement rake, and technical effects of the method may also refer to technical effects of the relevant parts of the total pressure measurement rake, and are not described herein again.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (9)
1. A total pressure measurement rake, comprising:
the cross section of the inner wall of the sleeve (1) is of a special-shaped structure, and the outer wall of one end of the sleeve is provided with an annular connecting edge;
one end of the inner branch pipe (2) extends into the other end of the sleeve (1), and the outer wall of the inner branch pipe is at least partially attached to the inner wall of the sleeve (1);
one side of the adapter ring (3) is connected with the annular connecting edge, and the other side of the adapter ring is provided with an adapter edge;
one end of the outer branch pipe (4) extends into the sleeve pipe (1) from the end back to the inner branch pipe (2), and the end is in threaded fit connection with the end, extending into the sleeve pipe (1), of the inner branch pipe (2);
the clamp (5) is connected with the switching edge and clamps the outer branch pipe (4);
the total pressure measuring head (6) is connected to the other end of the inner branch pipe (2), is provided with a communication hole and a plurality of total pressure measuring holes; the communication hole is communicated with the interior of the inner branch pipe (2) and each total pressure measuring hole; each total pressure measuring hole is distributed in an arc shape;
and each thin-wall metal air guide pipe (7) is provided with one end of each thin-wall metal air guide pipe (6) extending into the other end of the outer branch pipe (4), penetrates through the inner branch pipe (2), extends into the communication hole, is connected to the total pressure measuring head (5), and is correspondingly communicated with one total pressure measuring hole.
2. The total pressure measurement rake of claim 1,
the two switching edges are distributed on two sides of the sleeve (1).
3. The total pressure measurement rake of claim 1,
the outer wall of the outer branch pipe (4) is provided with a plurality of annular clamping grooves; each annular clamping groove is axially distributed along the outer branch pipe (4);
the clamping hoop (5) is clamped in one annular clamping groove.
4. The total pressure measurement rake of claim 1,
and pure calcium aluminate high-temperature cement is filled in the space between the communication hole and each total pressure measuring hole.
5. The total pressure measurement rake of claim 1,
said total pressure measuring head (6) comprising:
an arc-shaped plate (8), one side of which is connected with one end of the inner branch pipe (2) back to the sleeve (1), and the side is provided with the communication hole;
the total pressure measuring holes are distributed on one arc-shaped edge of the arc-shaped plate (8).
6. Total pressure measurement rake according to claim 5,
the total pressure measuring head (6) further comprises:
the connecting plate (9) is connected to one side, back to the inner branch pipe (2), of the arc-shaped plate (8), and a communicating cavity is formed between the connecting plate and the inner branch pipe (2); the communicating cavity is communicated with the communicating hole and each total pressure measuring hole.
7. The total pressure measurement rake of claim 1,
further comprising:
a plurality of cowlings (10) are connected on total pressure measuring head (6), every cowling (10) correspond and cover one total pressure measuring hole, its front end have with correspond total pressure measuring hole intercommunication's inlet port, the lateral wall has a plurality of exhaust holes along circumference distribution.
8. The total pressure measurement rake of claim 1,
the windward angle of each air inlet is 90 degrees.
9. A method for measuring total pressure in an aircraft engine flow passage is characterized by comprising the following steps:
the sleeve (1) extends into an aircraft engine flow channel from the outer side of an aircraft engine casing (11) through an opening on the aircraft engine casing (11), and an annular connecting edge on the sleeve is connected to the outer side of the aircraft engine casing (11);
extending the inner branch pipe (2) into the sleeve (1) from the flow passage of the aircraft engine;
the outer branch pipe (4) extends into the sleeve (1) from the outer side of the aeroengine casing (11) and is in threaded fit connection with the inner branch pipe (2);
the outer branch pipe (4) is hooped by a hoop (5);
wherein,
the adapter ring (3) is connected to the connecting edge;
the clamp (5) is connected to the switching edge;
the total pressure measuring head (6) is connected to the inner branch pipe (2);
each thin-wall metal gas-guiding pipe (7) is connected to a total pressure measuring head (6) and is led out through an inner branch pipe (2) and an outer branch pipe (4);
when the clamp (5) is loosened, the radial position of the total pressure measuring head (6) in the aircraft engine flow channel can be adjusted by pushing and pulling the outer branch pipe (4) from the outer side of the aircraft engine casing (11), and after the total pressure measuring head is adjusted to the position, the clamp (5) is used for clamping the outer branch pipe (4) again, so that the total pressure measurement of each radial position in the aircraft engine flow channel can be realized.
Priority Applications (1)
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| CN118408673A (en) * | 2024-06-28 | 2024-07-30 | 中国航发四川燃气涡轮研究院 | Method and system for correcting total pressure of inlet of air compressor based on intermediate casing loss model |
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| CN114441089B (en) | 2023-08-22 |
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Effective date of registration: 20240523 Address after: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Patentee after: SHENYANG HANGFA TECHNOLOGY INDUSTRIAL Co.,Ltd. Country or region after: China Address before: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Patentee before: AECC SHENYANG ENGINE Research Institute Country or region before: China |