CN116519312A - Total pressure measuring probe for high-pressure turbine outlet of aero-engine - Google Patents
Total pressure measuring probe for high-pressure turbine outlet of aero-engine Download PDFInfo
- Publication number
- CN116519312A CN116519312A CN202310482422.6A CN202310482422A CN116519312A CN 116519312 A CN116519312 A CN 116519312A CN 202310482422 A CN202310482422 A CN 202310482422A CN 116519312 A CN116519312 A CN 116519312A
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- Prior art keywords
- pressure
- pressure sensing
- turbine outlet
- casting process
- pressure turbine
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- 239000000523 sample Substances 0.000 title claims abstract description 23
- 238000005266 casting Methods 0.000 claims abstract description 19
- 239000000463 material Substances 0.000 claims abstract description 14
- 238000012546 transfer Methods 0.000 claims abstract description 14
- 230000000903 blocking effect Effects 0.000 claims abstract description 9
- 239000013078 crystal Substances 0.000 claims abstract description 5
- 238000005259 measurement Methods 0.000 claims description 12
- 238000003466 welding Methods 0.000 claims description 2
- 238000009530 blood pressure measurement Methods 0.000 abstract description 12
- 238000001816 cooling Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000009420 retrofitting Methods 0.000 description 1
Classifications
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- 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
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The application belongs to the technical field of aero-engine high-pressure turbine outlet total pressure measurement, and in particular relates to an aero-engine high-pressure turbine outlet total pressure measurement probe, which comprises: the support rod is cast by single-crystal high-temperature resistant materials, is in a blade shape, is provided with a mounting boss on the outer wall of the top end, is provided with a plurality of conical pressure sensing holes distributed along the axial direction of the support rod at the front edge, is internally provided with a plurality of pressure sensing channels, and is provided with a plurality of groups of casting process holes on the side wall; each pressure sensing channel is communicated with each group of casting process holes, the tail end of each pressure sensing channel is communicated with each conical pressure sensing hole, and the upper end of each pressure sensing channel extends to the top end of each supporting rod; a plurality of groups of blocking blocks made of monocrystalline high temperature resistant material and blocked in each group of casting process holes; the plurality of transfer tubes are made of monocrystalline high-temperature resistant materials, one ends of the transfer tubes are connected to the top ends of the support rods and are communicated with the top ends of the pressure sensing channels; one end of each pressure measuring tube is connected with the other end of each transfer tube; and the pressure connectors are connected to the other ends of the pressure measuring pipes.
Description
Technical Field
The application belongs to the technical field of total pressure measurement of an aero-engine high-pressure turbine outlet, and particularly relates to a total pressure measurement probe for an aero-engine high-pressure turbine outlet.
Background
The total pressure of the high-pressure turbine outlet of the aeroengine is an important performance index, and because the temperature and the pressure of the flow field of the high-pressure turbine outlet are higher, the structure of the high-pressure turbine and the low-pressure turbine is compact, the space is narrow, and currently, the total pressure of the high-pressure turbine outlet is mainly measured based on the refitting of the guide blades of the low-pressure turbine.
The method comprises the steps of refitting a low-pressure turbine guide blade of an aeroengine, wherein a plurality of mounting holes are formed in the front edge of the low-pressure turbine guide blade along the axial direction of the low-pressure turbine guide blade, the aperture of each mounting hole is about 2mm, one end of each pressure measuring tube stretches into a cooling cavity of the low-pressure turbine guide blade, the aperture of each pressure measuring tube stretches out about 3mm and is welded with the low-pressure turbine guide blade, the other end of each pressure measuring tube is led out from the blade crown of the low-pressure turbine guide blade, passes through a lead hole formed in a casing of the aeroengine, is led out to the outside of the casing, and is connected with a pressure acquisition system to measure total pressure, so that the following defects exist in the technical scheme as shown in fig. 1:
1) The low-pressure turbine guide blade is required to be provided with a mounting hole, so that the strength of the low-pressure turbine guide blade can be damaged, the aerodynamic performance of the low-pressure turbine guide blade is affected, and the low-pressure turbine guide blade can not be used continuously after the total pressure measurement is completed;
2) The positions of the measuring points are concentrated at the front edge of the low-pressure turbine guide vane, so that the total pressure distribution of the flow field of the outlet of the high-pressure turbine cannot be comprehensively measured;
3) The pressure sensing is carried out at the part of the pressure measuring pipe extending out of the mounting hole, and the pressure measuring pipe is a thin metal pipe, so that the flow field at the outlet of the high-pressure turbine is greatly disturbed, and the pressure measuring pipe is easy to ablate in a high-temperature environment, and in addition, the insensitive range of total pressure measurement is small;
4) The pressure measuring pipe is welded with the low-pressure turbine guide vane and is in a high-temperature environment, and the weld joint part is subjected to high-temperature ablation;
5) The pressure measuring pipe is led out through the cooling cavity of the low-pressure turbine guide vane, so that the operation is difficult, the cooling cavity is blocked, the cooling effect of the low-pressure turbine guide vane is affected, and the low-pressure turbine guide vane is damaged by high temperature;
6) The pressure measurement pipe draws along journey and need to carry out the preforming with a plurality of places and fix, and is time consuming hard.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine high pressure turbine outlet measurement total pressure probe that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft engine high pressure turbine outlet measurement total pressure probe comprising:
the support rod is cast by single-crystal high-temperature resistant materials, is in a blade shape, is provided with a mounting boss on the outer wall of the top end, is provided with a plurality of conical pressure sensing holes distributed along the axial direction of the support rod at the front edge, is internally provided with a plurality of pressure sensing channels, and is provided with a plurality of groups of casting process holes on the side wall; each pressure sensing channel is communicated with each group of casting process holes, the tail end of each pressure sensing channel is communicated with each conical pressure sensing hole, and the upper end of each pressure sensing channel extends to the top end of each supporting rod;
a plurality of groups of blocking blocks made of monocrystalline high temperature resistant material and blocked in each group of casting process holes;
the plurality of transfer tubes are made of monocrystalline high-temperature resistant materials, one ends of the transfer tubes are connected to the top ends of the support rods and are communicated with the top ends of the pressure sensing channels;
one end of each pressure measuring tube is connected with the other end of each transfer tube;
and the pressure connectors are connected to the other ends of the pressure measuring pipes.
According to at least one embodiment of the present application, in the above-mentioned aero-engine high-pressure turbine outlet measurement total pressure probe, each conical pressure sensing hole is opened toward the incoming flow direction, the depth is 4mm, and the cone angle is 60 °.
According to at least one embodiment of the present application, in the above-mentioned aircraft engine high-pressure turbine outlet measurement total pressure probe, each set of blocks is welded in each set of casting process holes;
each transfer tube is welded with each support rod and each pressure measuring tube;
and each pressure measuring pipe is connected with each pressure joint in a welding way.
According to at least one embodiment of the present application, in the above-mentioned total pressure probe for measuring the outlet of the high-pressure turbine of the aeroengine, each pressure measuring pipe is connected with a pin, and then is connected with a pressure acquisition system.
Drawings
FIG. 1 is a schematic illustration of a prior art retrofitting of an aircraft engine low pressure turbine guide vane to measure high pressure turbine outlet total pressure;
FIG. 2 is a schematic illustration of an aircraft engine high pressure turbine outlet measurement total pressure probe provided by an embodiment of the present application;
FIG. 3 is a schematic view of a strut provided in an embodiment of the present application;
FIG. 4 is a cross-sectional view of a strut provided by an embodiment of the present application;
FIG. 5 is a schematic partial cross-sectional view of a strut provided in an embodiment of the present application;
wherein:
1-a supporting rod; 2-blocking; 3-a transfer tube; 4-pressure measuring tube; 5-pressure tap.
For better illustration of the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-5.
An aircraft engine high pressure turbine outlet measurement total pressure probe comprising:
the support rod 1 is cast by single-crystal high-temperature resistant materials, is in a blade shape, is provided with a mounting boss on the outer wall of the top end, is provided with a plurality of conical pressure sensing holes distributed along the axial direction of the support rod, is internally provided with a plurality of pressure sensing channels, and is provided with a plurality of groups of casting process holes on the side wall; each pressure sensing channel is communicated with each group of casting process holes, the tail end of each pressure sensing channel is communicated with each conical pressure sensing hole, and the upper end of each pressure sensing channel extends to the top end of the supporting rod 1;
a plurality of groups of blocking blocks 2 which are made of monocrystalline high-temperature resistant materials and are blocked in each group of casting process holes;
a plurality of transfer tubes 3 made of single-crystal high-temperature resistant material, one ends of which are connected to the top ends of the support rods 1 and communicated with the top ends of the pressure sensing channels;
one end of each pressure measuring tube 4 is connected with the other end of each transfer tube 3;
a plurality of pressure taps 5 are connected to the other ends of the respective pressure measuring tubes 4.
According to the disclosed aeroengine high-pressure turbine outlet measurement total pressure probe, when the total pressure at the high-pressure turbine outlet is measured, the mounting holes can be formed in the casing, the supporting rod 1 passes through the mounting holes, the mounting bosses are connected to the casing by the bolts for fixing, the airflow at the high-pressure turbine outlet can pass through the conical pressure sensing holes, the airflow can be led into the pressure measuring pipe 4 through the pressure sensing channels and the switching pipe 3, and is led out through the pressure measuring pipe 4, and then is connected to the pressure collecting system through the pressure connector 5 for data collection, so that the total pressure at the high-pressure turbine outlet is measured.
For the total pressure measuring probe for the high-pressure turbine outlet of the aeroengine disclosed in the above embodiment, it can be understood by those skilled in the art that, in specific application, only the supporting rod 1 and the blocking 2 are directly in a high-temperature environment, the supporting rod 1 and the blocking 2 are made of monocrystalline high-temperature resistant materials, high-temperature corrosion can be resisted, and each pressure measuring tube 4 is designed to be connected with the supporting rod 1 through the switching tube 3 made of monocrystalline high-temperature resistant materials, so that the pressure measuring tube 4 can be protected from high-temperature damage, and in addition, the supporting rod 1 is designed into a blade shape, so that the interference on a flow field can be reduced.
For the total pressure measuring probe for the high-pressure turbine outlet of the aeroengine disclosed by the embodiment, as can be understood by those skilled in the art, the design of the total pressure measuring probe utilizes the conical pressure sensing holes formed on the front edge of the supporting rod 1 along the axial direction of the supporting rod to bleed air, so that the bleed air range can be enlarged, the insensitive range for total pressure measurement can be enlarged, and the accuracy for total pressure measurement of the high-pressure turbine outlet can be ensured.
For the total pressure measuring probe for the high-pressure turbine outlet of the aeroengine disclosed by the embodiment, those skilled in the art can understand that the side wall of the supporting rod 1 is designed to be provided with a plurality of groups of casting process holes communicated with each pressure sensing channel, so that the internal grinding tool can be supported in the casting process of the supporting rod 1, the casting forming of the supporting rod 1 is facilitated, and after casting is completed, the blocking block 2 is used for blocking, so that the smoothness of each pressure sensing channel is ensured.
In some optional embodiments, in the above-mentioned air engine high-pressure turbine outlet total pressure measurement probe, each conical pressure sensing hole is opened towards the incoming flow direction, its axis is designed to be parallel to the airflow direction of the position where it is located, the depth is 4mm, the cone angle is 60 °, so as to increase the insensitive range of total pressure measurement, ensure the accuracy of total pressure measurement of the high-pressure turbine outlet, and each conical pressure sensing hole can be distributed along the radial direction of the air engine along an equal torus.
In some alternative embodiments, in the above-mentioned aircraft engine high-pressure turbine outlet measurement total pressure probe, each set of blocks 2 is welded in each set of casting process holes;
each transfer tube 3 is welded and connected with each support rod 1 and each pressure measuring tube 4;
and each pressure measuring pipe 4 is welded with each pressure joint 5.
In some alternative embodiments, in the above-mentioned total pressure probe for measuring the outlet of the high-pressure turbine of the aeroengine, each pressure measuring tube 4 is connected with a pin, and then is connected with a pressure acquisition system.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (4)
1. An aircraft engine high pressure turbine outlet measurement total pressure probe, comprising:
the support rod (1) is cast by single-crystal high-temperature resistant materials, is in a blade shape, is provided with a mounting boss on the outer wall of the top end, is provided with a plurality of conical pressure sensing holes distributed along the axial direction of the support rod, is internally provided with a plurality of pressure sensing channels, and is provided with a plurality of groups of casting process holes on the side wall; each pressure sensing channel is communicated with each group of casting process holes, the tail end of each pressure sensing channel is communicated with each conical pressure sensing hole, and the upper end of each pressure sensing channel extends to the top end of the supporting rod (1);
a plurality of groups of blocking blocks (2) which are made of monocrystalline high-temperature resistant materials and are blocked in each group of casting process holes;
a plurality of transfer tubes (3) made of monocrystalline high temperature resistant material, one ends of which are connected to the top ends of the support rods (1) and communicated with the top ends of the pressure sensing channels;
one end of each pressure measuring tube (4) is connected with the other end of each transfer tube (3);
and a plurality of pressure connectors (5) connected to the other ends of the pressure measuring pipes (4).
2. The aircraft engine high pressure turbine outlet measurement total pressure probe of claim 1,
the openings of the conical pressure sensing holes face the incoming flow direction, the depth is 4mm, and the cone angle is 60 degrees.
3. The aircraft engine high pressure turbine outlet measurement total pressure probe of claim 1,
each group of blocking blocks (2) is welded in each group of casting process holes;
each transfer tube (3) is welded with each support rod (1) and each pressure measuring tube (4);
and each pressure measuring pipe (4) is connected with each pressure joint (5) in a welding way.
4. The aircraft engine high pressure turbine outlet measurement total pressure probe of claim 1,
and each pressure measuring pipe (4) is connected with a contact pin, and then is connected with a pressure acquisition system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310482422.6A CN116519312A (en) | 2023-04-30 | 2023-04-30 | Total pressure measuring probe for high-pressure turbine outlet of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310482422.6A CN116519312A (en) | 2023-04-30 | 2023-04-30 | Total pressure measuring probe for high-pressure turbine outlet of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116519312A true CN116519312A (en) | 2023-08-01 |
Family
ID=87395509
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310482422.6A Pending CN116519312A (en) | 2023-04-30 | 2023-04-30 | Total pressure measuring probe for high-pressure turbine outlet of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116519312A (en) |
-
2023
- 2023-04-30 CN CN202310482422.6A patent/CN116519312A/en active Pending
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