CN117345414A - Aeroengine combustion chamber system and aeroengine - Google Patents
Aeroengine combustion chamber system and aeroengine Download PDFInfo
- Publication number
- CN117345414A CN117345414A CN202210742466.3A CN202210742466A CN117345414A CN 117345414 A CN117345414 A CN 117345414A CN 202210742466 A CN202210742466 A CN 202210742466A CN 117345414 A CN117345414 A CN 117345414A
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- China
- Prior art keywords
- temperature measuring
- combustion chamber
- cylinder
- sliding block
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 60
- 238000009434 installation Methods 0.000 claims abstract description 17
- 238000007789 sealing Methods 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 238000009529 body temperature measurement Methods 0.000 abstract description 10
- 238000000034 method Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000003466 welding Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000009414 blockwork Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
- G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The invention discloses an aeroengine combustion chamber system and an aeroengine, wherein the aeroengine combustion chamber system comprises a combustion chamber outer casing; a flame tube located radially inside the combustion chamber outer casing; the temperature measuring device comprises an installation part fixedly connected with the combustion chamber outer casing, a guide pipe fixedly connected with the installation part, a temperature measuring strip, a sliding block fixedly connected with the temperature measuring strip and slidable along the radial direction relative to the installation part, and an elastic device arranged between the sliding block and the installation part; the guide tube includes the passageway that extends towards the flame tube, and the temperature measurement strip is including being located the radial inboard temperature measurement section of sliding block, and the temperature measurement section is located the passageway of guide tube, and the temperature measurement section includes the temperature measurement end that contacts with the flame tube wall of flame tube in order to be used for measuring the temperature of flame tube wall, and temperature measuring device is configured to: the channel guides the telescopic movement of the temperature measuring section relative to the guide tube, and the elastic force provided by the elastic device to the sliding block enables the temperature measuring section to extend out of the channel and enables the temperature measuring end to press the flame tube wall.
Description
Technical Field
The invention relates to the field of aero-machinery, in particular to an aero-engine combustion chamber system and an aero-engine.
Background
In the development process of an aeroengine, a temperature measuring device is often adopted to monitor the temperature of the flame tube wall of the flame tube of the combustion chamber of the aeroengine, so that the temperature of the flame tube wall of the flame tube does not exceed a limit value in the test process, the safety of the test is ensured, and the wall surface is generally measured by the contact type temperature measuring device. With the development of products, for example, the thrust-weight ratio of an engine is continuously improved, the temperature rise of a combustion chamber is also continuously improved, and the requirements on the temperature measurement reliability of a temperature measuring device on the wall surface of a flame tube are also higher. The combustion chamber of the aeroengine sometimes has the conditions of larger vibration and the like, and whether the temperature measuring device can be reliably contacted with the wall surface is very important for safety guarantee.
Disclosure of Invention
The invention aims to provide an aeroengine combustion chamber system and an aeroengine, which can reliably measure the temperature of the flame tube wall of a flame tube.
The invention discloses an aeroengine combustion chamber system, comprising:
a combustion chamber outer casing;
the flame tube is positioned on the inner side of the combustion chamber outer casing along the radial direction;
the temperature measuring device comprises an installation part fixedly connected with the combustion chamber outer casing, a guide pipe fixedly connected with the installation part, a temperature measuring strip, a sliding block fixedly connected with the temperature measuring strip and slidable along the radial direction relative to the installation part, and an elastic device arranged between the sliding block and the installation part;
wherein the guide tube comprises a channel extending towards the flame tube, the temperature measuring strip comprises a temperature measuring section located at the radial inner side of the sliding block, the temperature measuring section is located in the channel of the guide tube, and the temperature measuring section comprises a temperature measuring end contacted with the flame tube wall of the flame tube for measuring the temperature of the flame tube wall, and the temperature measuring device is configured to: the channel guides the temperature measuring section to move in a telescopic mode relative to the guide tube, and the elastic device enables the temperature measuring section to extend out of the channel and enables the temperature measuring end to press the flame tube wall due to elastic force provided by the sliding block.
In some embodiments, the mounting portion includes a first cylinder, the sliding block is located in a cylinder cavity of the first cylinder and is slidably connected to a cylinder wall of the first cylinder, and the elastic device includes a compression spring disposed between the cylinder wall of the first cylinder and the sliding block.
In some embodiments, the guide tube is cylindrical, the diameter of the guide tube is smaller than the diameter of the first cylinder, and one end of the guide tube is in sealing connection with the first cylinder.
In some embodiments, the first cylinder is located radially outward of the combustion chamber outer casing, and the guide pipe is connected to the first cylinder through a conical connecting pipe that is located radially outward of the combustion chamber outer casing and is not in contact with the combustion chamber outer casing.
In some embodiments, the first barrel and the guide tube each extend radially.
In some embodiments, the mounting portion further includes a second cylinder sleeved outside the first cylinder, and the second cylinder is fixedly connected with the combustion chamber outer casing.
In some embodiments, the mounting portion further comprises an end cap fixedly connected to the ends of the first and second barrels simultaneously, the end cap forming the barrel walls of the first and second barrels.
In some embodiments, the temperature measuring strip passes through the wall of the first barrel in the radial direction, the temperature measuring strip is fixedly connected with the wall of the first barrel, and the part of the temperature measuring strip between the wall of the first barrel and the sliding block has flexibility.
In some embodiments, the temperature measuring strip passes through the wall of the first barrel in the radial direction, the shell of the temperature measuring strip is a rigid shell, and the shell of the temperature measuring strip is in sliding sealing fit with the wall of the first barrel.
In some embodiments, the temperature bar comprises a thermocouple.
In a second aspect, the invention discloses an aircraft engine comprising any of the aircraft engine combustion chamber systems described.
According to the aeroengine combustion chamber system provided by the invention, the temperature measuring device comprising the guide pipe, the temperature measuring strip, the sliding block and the elastic device is arranged, when the flame cylinder wall of the flame cylinder is subjected to temperature measurement, the guide pipe can conduct guiding limiting on the movement of the temperature measuring strip, the elastic device can drive the temperature measuring end of the temperature measuring strip to press the flame cylinder wall through the sliding block by applying elastic force to the sliding block, and the flame cylinder wall of the flame cylinder can be reliably pressed under the condition that the aeroengine combustion chamber system has some vibration, so that the flame cylinder wall of the flame cylinder is reliably subjected to temperature measurement.
Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 is a schematic view of a portion of an aircraft engine combustion chamber system according to an embodiment of the present invention;
FIG. 2 is a schematic view of a portion of an aircraft engine combustion chamber system of other embodiments;
fig. 3 is a schematic cross-sectional view of the structure shown in fig. 2.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
In the description of the present invention, it should be understood that the terms "first," "second," and the like are used for defining the components, and are merely for convenience in distinguishing the corresponding components, and the terms are not meant to have any special meaning unless otherwise indicated, so that the scope of the present invention is not to be construed as being limited.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
The aircraft engine combustor system of the present embodiment is used in some embodiments to measure and test an aircraft engine, i.e., is a test component of an aircraft engine. In some embodiments, the aircraft engine combustion chamber system may be part of a normally operating aircraft engine, i.e. a working component of the aircraft engine. The radial direction of the application is not specially described, and the reference is made by taking the central line of the combustion chamber system of the aero-engine as the central line, and when the combustion chamber system of the aero-engine is a part of the aero-engine which works normally, the central line of the combustion chamber system of the aero-engine is overlapped with the central line of the aero-engine, the central lines of the compressor, the turbine and the like of the aero-engine. As shown in fig. 1 to 3, the aircraft engine combustion chamber system of the present embodiment includes a combustion chamber outer casing 1, a flame tube, and a temperature measuring device.
The combustion chamber outer casing 1 is radially outward of the liner. The flame tube is used for burning fuel oil to generate flame, and is positioned on the inner side of the combustion chamber outer casing 1 along the radial direction.
As shown in fig. 2 and 3, the temperature measuring device comprises an installation part fixedly connected with the combustion chamber outer casing 1, a guide tube 6 fixedly connected with the installation part, a temperature measuring strip 3, a sliding block 7 fixedly connected with the temperature measuring strip 3 and slidable along the radial direction relative to the installation part, and an elastic device 8 arranged between the sliding block 7 and the installation part.
As shown in fig. 2 and 3, the guide tube 6 includes a channel extending toward the flame tube in the embodiment shown, the guide tube 6 is a closed elongated circular tube, the guide tube 6 is circular in cross-section, the channel is an elongated circular hole in the elongated circular tube, and the channel is circular in cross-section. In some embodiments not shown in the drawings, the guide tube 6 is an unclosed arc-shaped tube, the guide tube 6 is arc-shaped in cross section, the channel is an elongated fan-shaped groove located in the elongated arc-shaped tube, and the fan-shaped groove is fan-shaped in cross section. The temperature measuring strip 3 comprises a temperature measuring section 32 positioned on the radial inner side of the sliding block 7, and the temperature measuring section 32 is positioned in the channel of the guide tube 6. The temperature measuring section 32 includes a temperature measuring end that contacts the flame tube wall 2 of the flame tube for measuring the temperature of the flame tube wall 2, the temperature measuring device being configured to: the channel guides the telescopic movement of the temperature measuring section 32 relative to the guide tube 6, and the elastic force provided by the elastic device 8 to the sliding block 7 causes the temperature measuring section 32 to tend to extend out of the channel and causes the temperature measuring end to press against the flame tube wall 2. The temperature measuring section 32 is also in a long strip shape, and after being positioned in the long strip-shaped channel, the channel limits and guides the movement of the temperature measuring section 32, and under the guiding action of the channel, the temperature measuring section 32 can only stretch and retract along the extending direction of the channel. The elastic device 8 applies elastic force to the sliding block 7 to drive the sliding block 7 to compress tightly towards the direction close to the flame tube wall 2, so that a temperature measuring strip fixedly connected with the sliding block 7 can be driven to drive a temperature measuring section to compress tightly the flame tube wall 2, and the temperature measuring end is tightly attached to the flame tube wall 2 to measure the temperature.
According to the aeroengine combustion chamber system, through the arrangement of the temperature measuring device comprising the guide tube 6, the temperature measuring strip 3, the sliding block 7 and the elastic device 8, when the flame tube wall 2 of the flame tube is subjected to temperature measurement, the guide tube 6 can conduct guiding limiting on the movement of the temperature measuring strip 3, the elastic device 8 can drive the temperature measuring end of the temperature measuring strip 3 to press the flame tube wall 2 through the sliding block 7 by applying elastic force to the sliding block 7, and the flame tube wall 2 of the flame tube can be reliably pressed under the condition that the aeroengine combustion chamber system has some vibration, and the flame tube wall 2 of the flame tube can be reliably subjected to temperature measurement.
In some embodiments, as shown in fig. 3, in order to enable the elastic means to apply an elastic force to the sliding block in a stable direction, the mounting portion includes a first cylinder 9, the sliding block 7 is located in a cylinder cavity of the first cylinder 9 and is slidably connected to a cylinder wall of the first cylinder 9, and the elastic means 8 includes a compression spring disposed between the cylinder wall of the first cylinder 9 and the sliding block 7. The sliding block 7 of the embodiment is more stable, reduces disturbance to the temperature measuring strip, and improves the temperature measuring stability of the temperature measuring device.
In some embodiments, to reduce disturbance to the temperature measuring strip, as shown in fig. 2 and 3, the guide tube 6 is cylindrical, the diameter of the guide tube 6 is smaller than that of the first cylinder 9, and one end of the guide tube 6 is in sealing connection with the first cylinder 9. This arrangement enables the strip 3 to be in a relatively isolated environment, which helps to reduce the effects of the external environment and improves the measurement stability of the strip.
In some embodiments, to reduce heat transfer to the elastic means and the sliding block by the high temperature of the combustion chamber housing 1, the first cylinder 9 is located radially outside the combustion chamber housing 1, the guide tube 6 is connected to the first cylinder 9 by a conical connecting tube 69, and the conical connecting tube 69 is located radially outside the combustion chamber housing 1 and is not in contact with the combustion chamber housing 1. The conical connecting pipe 69 is arranged to enable the connection of the first cylinder 9 and the guide pipe 6 to be stable, structural stress is reduced, meanwhile, the conical connecting pipe 69 can limit the position of the sliding block 7, so that the extension of the temperature measuring strip relative to the guide pipe is limited, the temperature measuring section of the temperature measuring section 32 is protected, and the flame cylinder wall 2 is prevented from being too tightly pressed to crush the flame cylinder wall 2. In order to make the compression of the temperature measuring section against the wall 2 of the flame tube more reliable by the elastic force of the elastic means, in the embodiment shown in the figures, both the first cylinder 9 and the guide tube 6 extend in radial direction.
In some embodiments, in order to improve the protection of the elastic device and the sliding block and make the elastic device and the sliding block work stably, the installation part further comprises a second cylinder 5 sleeved outside the first cylinder 9, and the second cylinder 5 is fixedly connected with the combustion chamber outer casing 1. The second cylinder 5 is arranged to block external air flow, so that disturbance and influence on the elastic device and the sliding block are reduced.
In some embodiments, the mounting portion further comprises an end cap 4 fixedly connected to the ends of the first cylinder 9 and the second cylinder 5 at the same time, the end cap 4 forming the walls of the first cylinder 9 and the second cylinder 5. In some embodiments, the end cap 4 is non-detachably fixedly connected to the second cylinder 5 at a first connection 41 and to the first cylinder 9 at a second connection 42 by welding or the like. In other embodiments, the end cap 4 is detachably screwed to the second cylinder 5 at the first connection 41 and to the first cylinder 9 at the second connection 42 by welding or the like.
In some embodiments, the temperature measuring strip 3 passes through the wall of the first barrel 9 in the radial direction, the temperature measuring strip 3 is fixedly connected with the wall, and a part of the temperature measuring strip 3 between the wall and the sliding block 7 is a flexible part 31, the flexible part 31 has flexibility, in this embodiment, the temperature measuring strip 3 and the wall of the first barrel 9 are fixedly connected at a third connection part 43 by welding or cementing, etc., the flexible part 31 is elastically stretchable, or the flexible part 31 is bendable, and the flexible part 31 may be a coiled flexible strip arranged in the first barrel 9.
In some embodiments, the temperature measuring strip 3 comprises a thermocouple, the temperature measuring strip 3 passes through the wall of the first barrel 9 in the radial direction, the housing of the temperature measuring strip 3 is a rigid housing, and the housing of the temperature measuring strip 3 is in sliding sealing fit with the wall of the first barrel 9. In some embodiments, the temperature strip 3 is an armored thermocouple.
Also disclosed in some embodiments is an aircraft engine comprising any of the above aircraft engine combustion chamber systems.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same; while the invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that: modifications may be made to the specific embodiments of the present invention or equivalents may be substituted for part of the technical features thereof; without departing from the spirit of the invention, it is intended to cover the scope of the invention as claimed.
Claims (11)
1. An aircraft engine combustion chamber system, comprising:
a combustion chamber outer casing (1);
the flame tube is positioned on the inner side of the combustion chamber outer casing (1) along the radial direction;
the temperature measuring device comprises an installation part fixedly connected with the combustion chamber outer casing (1), a guide pipe fixedly connected with the installation part, a temperature measuring strip (3), a sliding block (7) fixedly connected with the temperature measuring strip (3) and capable of sliding along the radial direction relative to the installation part, and an elastic device (8) arranged between the sliding block (7) and the installation part;
wherein the guide tube comprises a channel extending towards the flame tube, the temperature measuring strip (3) comprises a temperature measuring section (32) located radially inside the sliding block (7), the temperature measuring section (32) is located in the channel of the guide tube, and the temperature measuring section (32) comprises a temperature measuring end in contact with the flame tube wall (2) of the flame tube for measuring the temperature of the flame tube wall (2), the temperature measuring device is configured to: the channel guides the telescopic movement of the temperature measuring section (32) relative to the guide pipe, and the elastic force provided by the elastic device (8) to the sliding block (7) enables the temperature measuring section (32) to tend to extend out of the channel and enables the temperature measuring end to press the flame tube wall (2).
2. The aircraft engine combustion chamber system of claim 1, wherein the mounting comprises a first cylinder (9), the sliding block (7) being located in a cylinder cavity of the first cylinder (9) and being slidingly connected to a cylinder wall of the first cylinder (9), the elastic means (8) comprising a compression spring provided between the cylinder wall of the first cylinder (9) and the sliding block (7).
3. The aircraft engine combustion chamber system of claim 2, characterized in that the guide tube is cylindrical, the diameter of the guide tube being smaller than the diameter of the first cylinder (9), one end of the guide tube being in sealing connection with the first cylinder (9).
4. An aircraft engine combustion chamber system according to claim 3, characterized in that the first cylinder (9) is located radially outside the combustion chamber housing (1), the guide tube being connected to the first cylinder (9) by a conical connecting tube which is located radially outside the combustion chamber housing (1) and is not in contact with the combustion chamber housing (1).
5. An aircraft engine combustion chamber system according to claim 3, wherein the first cylinder (9) and the guide tube each extend radially.
6. The aircraft engine combustion chamber system according to claim 2, characterized in that the mounting part further comprises a second cylinder (5) which is arranged outside the first cylinder (9), the second cylinder (5) being fixedly connected with the combustion chamber housing (1).
7. The aircraft engine combustion chamber system of claim 6, characterized in that the mounting further comprises an end cap (4) fixedly connected to the ends of the first cylinder (9) and the second cylinder (5) at the same time, the end cap (4) forming the walls of the first cylinder (9) and the second cylinder (5).
8. An aircraft engine combustion chamber system according to claim 2, wherein the temperature measuring strip (3) passes radially through the wall of the first barrel (9), the temperature measuring strip (3) being fixedly connected to the wall and the portion of the temperature measuring strip (3) located between the wall and the sliding block (7) being flexible.
9. The aircraft engine combustion chamber system of claim 2, characterized in that the temperature measuring strip (3) passes radially through the wall of the first cylinder (9), the housing of the temperature measuring strip (3) being a rigid housing, the housing of the temperature measuring strip (3) being in sliding sealing engagement with the wall of the first cylinder (9).
10. An aircraft engine combustion chamber system according to any one of claims 1 to 9, wherein the temperature measuring strip (3) comprises a thermocouple.
11. An aircraft engine comprising an aircraft engine combustion chamber system as claimed in any one of claims 1 to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210742466.3A CN117345414A (en) | 2022-06-28 | 2022-06-28 | Aeroengine combustion chamber system and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210742466.3A CN117345414A (en) | 2022-06-28 | 2022-06-28 | Aeroengine combustion chamber system and aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117345414A true CN117345414A (en) | 2024-01-05 |
Family
ID=89361851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210742466.3A Pending CN117345414A (en) | 2022-06-28 | 2022-06-28 | Aeroengine combustion chamber system and aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117345414A (en) |
-
2022
- 2022-06-28 CN CN202210742466.3A patent/CN117345414A/en active Pending
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