Detection device and method suitable for combustion parameters of aero-engine combustion part

Abstract

The invention provides a detection device and method suitable for combustion parameters of a combustion component of an aero-engine, and the detection device comprises a first housing which is provided with an air inlet channel on the inner wall, and the air inlet channel is configured to provide gas for combustion; the second shell communicates with the gas inlet channel, the second shell is configured to be provided with a combustion component, gas in the second shell enters the combustion component through gas inlet holes in the outer wall of the combustion component, and the gas is combusted between the outer wall and the inner wall of the combustion component; the driving part is rotatably arranged on the combustion part in a penetrating manner; and the detection part is arranged on the side, close to the air outlet of the combustion component, of the driving part and extends to the annular air outlet of the combustion component from the driving part, and the driving part drives the detection part to rotate many times so that the detection part can detect combustion parameters of multiple positions of the air outlet.

Description

Technical Field

[0001] The present disclosure relates to the technical field of combustion equipment, and in particular to a T4 temperature detection device and method suitable for combustion components of aircraft engines. Background Art

[0002] Measuring the distribution of combustion parameters at the outlet of the annular combustion chamber of an aircraft engine, such as temperature and pressure, can evaluate the combustion efficiency of the combustion chamber, ensure the uniformity of heat distribution, prevent overheating and thermal stress damage of turbine blades, and facilitate engine performance optimization and fault diagnosis. Therefore, measuring the distribution of combustion parameters at the outlet of the annular combustion chamber of an aircraft engine is of great significance to improving the overall performance of the engine.

[0003] However, in the prior art, due to the high temperature of the outlet section of the annular combustion chamber of the aircraft engine, the fast gas flow rate, and the high and low temperature distribution of the temperature field, it is difficult to accurately measure the combustion parameter distribution of the combustion chamber outlet section in real time without affecting the temperature field of the combustion chamber outlet section. Summary of the invention

[0004] In view of this, the present disclosure provides a detection device and method for combustion parameters of combustion components of aircraft engines, which are used to at least partially solve the above technical problems and can simulate the distribution of combustion parameters of the air outlet of an annular combustion chamber.

[0005] The present disclosure provides a detection device suitable for combustion parameters of a combustion component of an aircraft engine, comprising: a first shell, an air intake passage is formed on the inner wall of the first shell, and the air intake passage is configured to provide gas for combustion; a second shell, connected to the air intake passage, the second shell is configured to install the combustion component, the gas in the second shell enters the combustion component through the air intake hole on the outer wall of the combustion component, and the gas burns between the outer wall and the inner wall of the combustion component; a driving part, rotatably penetrated through the combustion component; a detection part, arranged on a side of the driving part close to the air outlet of the combustion component, and extended from the driving part to the annular air outlet of the combustion component, the driving part drives the detection part to rotate multiple times, so that the detection part detects the combustion parameters at multiple positions of the air outlet.

[0006] Optionally, the detection part includes: an annular bracket installed on one side of the driving part close to the air outlet of the combustion component; a plurality of detection units evenly distributed along the circumference of the annular bracket and extending radially, each of the detection units including a plurality of radially distributed detectors to detect combustion parameters in an annular section parallel to the air outlet, thereby obtaining a gradient distribution of the combustion parameters of the annular section in the radial direction.

[0007] Optionally, the combustion parameter includes temperature, the detection unit includes a temperature detection unit, the detector is a temperature sensor, and the temperature sensor is used to detect the temperature, thereby obtaining the temperature gradient distribution of the annular cross-section.

[0008] Optionally, the combustion parameter includes pressure, the detection unit includes a pressure detection unit, the detector is a pressure sensor, and the pressure sensor is used to detect the pressure, so as to obtain the pressure gradient distribution of the annular cross-section.

[0009] Optionally, an opening is formed on the second shell to allow an external oil pipe to enter, and the oil pipe is connected to the combustion component to provide fuel for combustion.

[0010] Optionally, a slot is formed on the first shell, and the oil pipe is clamped in the slot.

[0011] Optionally, the driving unit includes: a motor; a first transmission member connected to an output shaft of the motor; a second transmission member meshing with the first transmission member; and a transmission shaft installed between the second transmission member and the detection unit.

[0012] Optionally, a mounting seat is provided in the first shell, the mounting seat extends from the first shell to the second shell, the transmission shaft passes through the mounting seat, and the second transmission member is sleeved on the transmission shaft.

[0013] Optionally, a rotating disk is provided on one side of the transmission shaft close to the air outlet, and the detection unit is provided on the rotating disk.

[0014] Optionally, the detection device for combustion parameters of combustion components of an aircraft engine further includes: an exhaust portion, which is connected to the air outlet, and the post-combustion gas is discharged through the exhaust portion.

[0015] Optionally, a conical cover plate is formed on one side of the driving portion close to the exhaust portion, and the conical cover plate extends into the interior of the exhaust portion to guide the gas to flow toward the exhaust portion.

[0016] Optionally, a plurality of cold air inlets are formed on the first shell, and the external cooling device is connected to the cold air inlets.

[0017] The present disclosure also provides a method for detecting combustion parameters of a combustion component of an aircraft engine, comprising: constructing a detection device for combustion parameters of a combustion component of an aircraft engine as described above; using the detection device to provide gas and fuel for combustion to the combustion component and realize combustion; using a driving unit of the detection device to drive a detection unit located at an annular air outlet of the combustion component to rotate continuously at a predetermined time interval and a predetermined angle; and obtaining a gradient distribution of the combustion parameters of an annular cross section parallel to the air outlet in a radial direction when the number of rotations of each detection unit satisfies the following relationship:

[0018] M = (360 o / (N*α))-1; wherein, M is the number of rotations, N is the number of detection units, and α is the predetermined angle for each rotation.

[0019] According to the embodiment of the present disclosure, by providing an air intake passage, gas for combustion can be provided to the combustion component. By providing a second housing connected to the air intake passage, the combustion component can be installed and gas can be allowed to enter the combustion component, thereby simulating the combustion state of the annular combustion chamber when the engine is running. By providing a driving part, the detection part can be driven to rotate, so that the combustion parameters at multiple positions of the air outlet can be detected, and then the distribution of the combustion parameters of the air outlet of the annular combustion chamber can be simulated. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other objects, features and advantages of the present disclosure will become more apparent through the following description of the embodiments of the present disclosure with reference to the accompanying drawings, in which:

[0021] Figure 1 A cross-sectional view of a detection device according to an embodiment of the present disclosure is schematically shown.

[0022] Figure 2 A side view of a detection device according to an embodiment of the present disclosure is schematically shown.

[0023] Figure 3 A side view of a detection unit according to an embodiment of the present disclosure is schematically shown.

[0024] Figure 4 The temperature gradient distribution diagram according to an embodiment of the present disclosure is schematically shown.

[0025] Figure 5 A pressure gradient distribution diagram according to an embodiment of the present disclosure is schematically shown.

[0026] Reference numerals

[0027] 1. First shell; 11. Air inlet passage; 111. First part; 112. Second part; 12. Slot; 2. Second shell; 21. Opening; 3. Combustion component; 31. Air outlet; 4. Driving unit; 41. Motor; 42. First transmission member; 43. Second transmission member; 44. Transmission shaft; 45. Mounting seat; 46. Rotating disk; 5. Detection unit; 51. Detection unit; 52. Ring bracket; 511. Detector; 512. Temperature detection unit; 513. Pressure detection unit; 514. Temperature sensor; 515. Pressure sensor; 6. Exhaust unit; 61. Third shell; 62. Exhaust passage; 63. Cooling jacket; 64. Connecting piece; 65. Cooling pipe; 7. Conical cover plate; 8. Cold air inlet. DETAILED DESCRIPTION

[0028] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the present disclosure. In the following detailed description, for ease of explanation, many specific details are set forth to provide a comprehensive understanding of the embodiments of the present disclosure. However, it is apparent that one or more embodiments may also be implemented without these specific details. In addition, in the following description, descriptions of known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present disclosure.

[0029] The terms used herein are only for describing specific embodiments and are not intended to limit the present disclosure. The terms "comprise", "include", etc. used herein indicate the existence of features, steps, operations and / or components, but do not exclude the existence or addition of one or more other features, steps, operations or components.

[0030] All terms (including technical and scientific terms) used herein have the meanings commonly understood by those skilled in the art unless otherwise defined. It should be noted that the terms used herein should be interpreted as having a meaning consistent with the context of this specification and should not be interpreted in an idealized or overly rigid manner.

[0031] When using expressions such as "at least one of A, B, and C, etc.", they should generally be interpreted according to the meaning of the expression commonly understood by those skilled in the art (for example, "a system having at least one of A, B, and C" should include but is not limited to a system having A alone, B alone, C alone, A and B, A and C, B and C, and / or A, B, C, etc.).

[0032] Figure 1 A cross-sectional view of a detection device according to an embodiment of the present disclosure is schematically shown. Figure 2 A side view of a detection device according to an embodiment of the present disclosure is schematically shown. Figure 3A side view of a detection unit according to an embodiment of the present disclosure is schematically shown.

[0033] like Figure 1-Figure 3 As shown, the embodiment of the present disclosure provides a detection device for combustion parameters of a combustion component 3 of an aircraft engine. The detection device may include a first shell 1, a second shell 2, a driving unit 4 and a detection unit 5. The first shell 1 and the second shell 2 may be cylindrical, respectively. An air intake passage 11 may be formed on the inner wall of the first shell 1. The air intake passage 11 is configured to provide gas for combustion. The air intake passage 11 may include a first portion 111 extending outwardly first horizontally and then obliquely, and a second portion 112 extending inwardly first horizontally and then obliquely. The first shell 1 may be a double-layer structure, and the first layer shell on the outer side and the second layer shell on the inner side may constitute the air intake passage 11. The first layer shell may surround the second layer shell. The second shell 2 may be connected to the air intake passage 11, that is, the combustion gas may enter the second shell 2. The second shell 2 is configured to install the combustion component 3. The gas in the second shell 2 may enter the combustion component 3 through the air intake hole on the outer wall of the combustion component 3. The gas burns between the outer wall and the inner wall of the combustion component 3. In detail, the combustion component 3 may be a flame tube in an annular combustion chamber. The combustion gas can burn in the flame tube to simulate the combustion state of the annular combustion chamber when the engine is running. The driving part 4 is rotatably arranged in the combustion component 3. The detection part 5 is arranged on the side of the driving part 4 close to the gas outlet 31 of the combustion component 3, and extends from the driving part 4 to the annular gas outlet 31 of the combustion component 3 to detect the combustion parameters near the annular gas outlet 31. The combustion parameters can be temperature and pressure, etc. The driving part 4 can drive the detection part 5 to rotate multiple times, so that the detection part 5 detects the combustion parameters at multiple positions of the gas outlet 31.

[0034] According to the embodiment of the present disclosure, by providing the air intake passage 11, gas for combustion can be provided to the combustion component 3. By providing the second housing 2 connected to the air intake passage 11, the combustion component 3 can be installed and gas can be allowed to enter the combustion component 3, so that the combustion state of the annular combustion chamber when the engine is running can be simulated. By providing the driving part 4, the detection part 5 can be driven to rotate, so that the combustion parameters of multiple positions of the air outlet 31 can be detected, and then the distribution of the combustion parameters of the air outlet 31 of the annular combustion chamber can be simulated.

[0035] In some embodiments, the detection part 5 may include an annular support 52 and a plurality of detection units 51. The annular support 52 may be installed on one side of the driving part 4 close to the gas outlet 31 of the combustion component 3, for example, sleeved or embedded on the driving part 4. The detection units 51 may be evenly distributed along the circumference of the annular support 52 and extend radially. Figure 3As shown, six detection units 51 may be provided. Each detection unit 51 may include a plurality of radially distributed detectors 511, that is, the distribution direction of the detectors 511 is the same as the extension direction of the detection unit 51. Since the driving unit 4 is arranged through the combustion component 3, the detection unit 5 is arranged on the side of the driving unit 4 close to the gas outlet 31 of the combustion component 3. When the detection unit 51 extends radially, the detection unit 51 may extend to a plane parallel to the gas outlet 31 and close to the gas outlet 31. Further, the detection unit 51 may extend to a position close to the outer edge of the gas outlet 31. Each detection unit 51 may detect combustion parameters in an annular cross section parallel to the gas outlet 31, thereby obtaining a gradient distribution of the combustion parameters of the annular cross section in the radial direction, so as to simulate the distribution of the combustion parameters of the gas outlet 31 of the annular combustion chamber. Furthermore, the combustion parameter distribution of the annular cross-section in the radial direction can be used to directly characterize the combustion parameter distribution of the annular combustion chamber outlet 31, and the combustion parameter distribution of the annular combustion chamber outlet 31 can also be obtained based on the gradient distribution of the combustion parameters of the annular cross-section in the radial direction.

[0036] Figure 4 The temperature gradient distribution diagram according to an embodiment of the present disclosure is schematically shown.

[0037] In some embodiments, the detection unit 51 may include a temperature detection unit 512. The detector 511 may be a temperature sensor 514. The temperature sensor 514 may be used to detect the temperature, thereby obtaining the temperature gradient distribution of the annular cross section. Figure 3-Figure 4 As shown, when each temperature detection unit 512 is provided with 3 temperature detection units 512 and each temperature detection unit 512 is provided with 5 temperature sensors 514, after the detection part 5 rotates 31 times from the initial position, each temperature sensor 514 can detect the pressure of 32 detection points in total, so that the temperature gradient distribution of 5 gradients (T01, T02, T03, T04 and T05) in 96 radial directions in the annular cross section can be detected, and a temperature field with 480 temperature data can be constructed, so that the temperature gradient distribution of the air outlet 31 of the annular combustion chamber can be simulated more accurately. The temperature sensor 514 can be a K-type thermocouple to ensure that the accurate detection temperature can be maintained under high temperature conditions.

[0038] Figure 5 A pressure gradient distribution diagram according to an embodiment of the present disclosure is schematically shown.

[0039] In some embodiments, the detection unit 51 may include a pressure detection unit 513. The detector 511 may be a pressure sensor 515. The pressure sensor 515 may be used to detect pressure, thereby obtaining a pressure gradient distribution of the annular cross section. Figure 3-Figure 5As shown, in the case where each pressure detection unit 513 is provided with three temperature detection units 512 and each temperature detection unit 512 is provided with three pressure sensors 515, when the detection portion 5 is rotated 31 times from the initial position, each pressure sensor 515 can detect the pressure of 32 detection points in total, thereby being able to detect the pressure gradient distribution of three gradients (P01, P02 and P03) in 96 radial directions within the annular cross-section, and being able to construct a pressure field with 288 pressure data, thereby being able to more accurately simulate the pressure gradient distribution of the air outlet 31 of the annular combustion chamber.

[0040] In some embodiments, an opening 21 for allowing an external oil pipe to enter may be formed on the second housing 2, and the oil pipe may be in communication with the combustion component 3 to provide fuel for combustion.

[0041] In some embodiments, a slot 12 may be formed on the first housing 1 , and the oil pipe may be clamped in the slot 12 to stably supply fuel to the combustion component 3 .

[0042] like Figure 1 As shown, in some embodiments, the driving part 4 may include a motor 41, a first transmission member 42, a second transmission member 43 and a transmission shaft 44. The first transmission member 42 may be connected to the output shaft of the motor 41. The first transmission member 42 may be connected to the output shaft of the motor 41 through a driving shaft. The driving shaft may extend through the side wall of the first shell 1 to the inside of the shell. The second transmission member 43 may mesh with the first transmission member 42. The transmission shaft 44 may be installed between the second transmission member 43 and the detection part 5. The transmission shaft 44 may extend through the first shell 1 and the second shell 2 in sequence to the air outlet 31. The detection part 5 may be installed on a side of the transmission shaft 44 close to the air outlet 31 (such as Figure 1 The right side of the middle transmission shaft 44).

[0043] Further, the first transmission member 42 and the second transmission member 43 may be bevel gears to precisely control the rotation of the detection unit 5. The transmission ratio of the first transmission member 42 and the second transmission member 43 may be 3:1. That is, when the driving shaft rotates one circle, the detection unit 5 rotates 120°. For example, the number of teeth of the first transmission member 42 may be 20. The number of teeth of the second transmission member 43 may be 60. In the case where the detection unit 5 needs to rotate 31 times to form the combustion parameters of the entire annular cross-section, the first transmission member 42 may rotate 11.25° each time, and the second transmission member 43 may rotate 3.75°. A reducer may be provided between the motor 41 and the transmission shaft 44 to precisely control the rotation of the transmission shaft 44. For example, when the motor rotates 5.99 circles, the transmission shaft 44 rotates 3.75°.

[0044] like Figure 1As shown, in some embodiments, a mounting seat 45 may be provided in the first housing 1. The mounting seat 45 may extend from the first housing 1 to the second housing 2, and the transmission shaft 44 may be inserted through the mounting seat 45. The second transmission member 43 may be sleeved on the transmission shaft 44. The mounting seat 45 may be connected to the inner wall of the first housing 1 (such as Figure 1 The upper and lower ends of the inner wall of the first shell 1 are connected, and when the driving part 4 drives the detecting part 5 to rotate, the driving part 4 and the detecting part 5 can be guaranteed to run smoothly.

[0045] like Figure 1 As shown, in some embodiments, a rotating disk 46 is provided on one side of the transmission shaft 44 close to the air outlet 31. The detection unit 5 can be installed on the rotating shaft through the dovetail groove of the rotating disk 46.

[0046] like Figure 1 As shown, in some embodiments, the detection device may further include an exhaust portion 6. The exhaust portion 6 may be in communication with the air outlet 31, and the gas after combustion may be discharged from the exhaust portion 6. The exhaust portion 6 may include a third shell 61. The third shell 61 may be in communication with the air outlet 31, and the gas after combustion may be discharged from the exhaust channel 62 formed by the third shell 61. A cooling jacket 63 surrounding the third shell 61 may be formed on the outside of the exhaust portion 6. The cooling jacket 63 may be in communication with a connecting piece 64 sleeved on the outer periphery of the cooling jacket 63. The connecting piece 64 may be in communication with a cooling pipe 65 arranged on the outer periphery of the cooling jacket 63. The coolant may enter the connecting piece 64 from the cooling pipe 65 and then enter the cooling jacket 63 to cool the gas in the exhaust channel 62.

[0047] like Figure 1 As shown, in some embodiments, a conical cover plate 7 is formed on one side of the driving part 4 close to the exhaust part 6. The conical cover plate 7 can be installed on the rotating disk 46. The conical cover plate 7 can extend to the inside of the exhaust part 6 to guide the gas to flow to the exhaust part 6.

[0048] like Figure 1 As shown, in some embodiments, a plurality of cold air inlets 8 may be formed on the first housing 1. An external cooling device may be connected to the cold air inlet 8 and the internal hollow transmission shaft 44 to provide cooling gas to the first housing 1. After the cooling gas enters the first housing 1 through the cold air inlet 8, it enters the transmission shaft 44 to cool the transmission shaft 44.

[0049] The embodiment of the present disclosure also provides a method for detecting combustion parameters of a combustion component of an aero-engine. The detection method may include the following steps S110 to S140.

[0050] S110: constructing a detection device suitable for combustion parameters of combustion components of an aircraft engine as described above.

[0051] S120: Use the detection device to provide gas and fuel for combustion to the combustion component 3 to achieve combustion.

[0052] S130: Using the driving part 4 of the detection device, drive the detection part 5 located at the annular air outlet 31 of the combustion component 3 to rotate continuously at a predetermined time interval and a predetermined angle.

[0053] S140 : When the number of rotations of each detection unit 51 satisfies the following relation (1), a gradient distribution of the combustion parameter in the radial direction of the annular cross section parallel to the air outlet 31 is obtained.

[0054] M = (360 o / (N*α))-1(1).

[0055] Where M is the number of rotations, N is the number of detection units, and α is the predetermined angle of each rotation. For example, if N is 3, α can be 10 o , then M can be 11. Further, when the flame tube has 12 flame ports, setting N to 3 and α to 3.75° can make each detection point located at the center of the flame, so that the combustion parameters can be obtained more accurately.

[0056] In some embodiments, the detection device may be connected to a data acquisition device for collecting electrical signals from the temperature sensor 514 and the pressure sensor 515 and converting the electrical signals into temperature signals and pressure signals. The data acquisition device may be connected to a data processing device, which may process and analyze the collected temperature signals and pressure signals, calculate the average temperature, single-point temperature, etc., so as to draw a temperature field distribution diagram and a pressure field distribution diagram at the air outlet 31.

[0057] In some embodiments, the control device can be used to control the rotation of the motor 41 to control the rotation of the detection unit 5. Specifically, take the control of the detection unit 5 to rotate 31 times, the predetermined time interval is 1 second, and the motor 41 rotates 5.99 times each time as an example. The motor 41 is controlled to rotate from the initial position. When the motor 41 reaches the measurement position, the detection unit 5 performs detection and the data acquisition device performs data acquisition. The detection and acquisition time may take a total of 1 second. After the data acquisition device completes data acquisition, the control device records the position number plus 1, and the motor 41 continues to rotate. Repeat the above operation until the position number is 31. When the position number is 31, the motor 41 is controlled to reverse at a constant speed, and the operating speed is 3 turns / second. When the motor 41 reverses and reaches the initial position and touches the limit switch, the motor 41 stops running. Parameters such as the current position and the number of positions are set to 0.

[0058] It will be appreciated by those skilled in the art that the features described in the various embodiments and / or claims of the present disclosure may be combined and / or combined in a variety of ways, even if such combinations and / or combinations are not explicitly described in the present disclosure. In particular, the features described in the various embodiments and / or claims of the present disclosure may be combined and / or combined in a variety of ways without departing from the spirit and teachings of the present disclosure. All of these combinations and / or combinations fall within the scope of the present disclosure.

[0059] The embodiments of the present disclosure are described above. However, these embodiments are only for the purpose of illustration and are not intended to limit the scope of the present disclosure. Although the embodiments are described above separately, this does not mean that the measures in the various embodiments cannot be used in combination to advantage. The scope of the present disclosure is defined by the attached claims and their equivalents. Without departing from the scope of the present disclosure, those skilled in the art may make various substitutions and modifications, which should all fall within the scope of the present disclosure.

Claims

1. A detection device for combustion parameters of combustion components of an aircraft engine, characterized in that: include: a first housing having an air intake passage formed on an inner wall thereof, the air intake passage being configured to provide gas for combustion; A second shell, connected to the air inlet passage, the second shell is configured to install the combustion component, the gas in the second shell enters the combustion component through the air inlet hole on the outer wall of the combustion component, and the gas burns between the outer wall and the inner wall of the combustion component; A driving part, rotatably disposed through the combustion component; The detection part is arranged on one side of the driving part close to the air outlet of the combustion component and extends from the driving part to the annular air outlet of the combustion component. The driving part drives the detection part to rotate multiple times so that the detection part detects the combustion parameters at multiple positions of the air outlet.

2. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: The detection part comprises: an annular bracket mounted on one side of the driving part close to the gas outlet of the combustion component; A plurality of detection units are evenly distributed along the circumference of the annular support and extend radially, and each of the detection units includes a plurality of radially distributed detectors to detect combustion parameters in an annular section parallel to the air outlet, thereby obtaining a gradient distribution of the combustion parameters of the annular section in the radial direction.

3. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 2, characterized in that: The combustion parameter includes temperature, the detection unit includes a temperature detection unit, the detector is a temperature sensor, and the temperature sensor is used to detect the temperature, so as to obtain the temperature gradient distribution of the annular cross section.

4. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 2 or 3, characterized in that: The combustion parameter includes pressure, the detection unit includes a pressure detection unit, the detector is a pressure sensor, and the pressure sensor is used to detect the pressure, so as to obtain the pressure gradient distribution of the annular cross section.

5. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: The second shell is formed with an opening for allowing an external oil pipe to enter, and the oil pipe is in communication with the combustion component to provide fuel for combustion; Preferably, a slot is formed on the first housing, and the oil pipe is clamped in the slot.

6. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: The driving unit comprises: Motor; A first transmission member connected to the output shaft of the motor; a second transmission member meshing with the first transmission member; and A transmission shaft, installed between the second transmission member and the detection part; Preferably, a mounting seat is provided in the first housing, the mounting seat extends from the first housing to the second housing, the transmission shaft passes through the mounting seat, and the second transmission member is sleeved on the transmission shaft; Preferably, a rotating disk is provided on one side of the transmission shaft close to the air outlet, and the detection unit is provided on the rotating disk.

7. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: Also includes: The exhaust part is communicated with the gas outlet, and the gas after combustion is discharged from the exhaust part.

8. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: A conical cover plate is formed on one side of the driving part close to the exhaust part, and the conical cover plate extends into the exhaust part to guide the gas to flow toward the exhaust part.

9. The detection device for combustion parameters of combustion components of an aircraft engine according to claim 1, characterized in that: A plurality of cold air inlets are formed on the first shell, and the external cooling device is communicated with the cold air inlets.

10. A method for detecting combustion parameters of combustion components of an aircraft engine, characterized in that: include: Constructing a detection device for combustion parameters of combustion components of an aircraft engine as described in any one of claims 2 to 9; Using the detection device to provide gas and fuel for combustion to the combustion component and achieve combustion; Using the driving part of the detection device, the detection part located at the annular air outlet of the combustion component is driven to rotate continuously at a predetermined time interval and a predetermined angle; When the number of rotations of each detection unit satisfies the following relationship, the gradient distribution of the combustion parameters in the radial direction of the annular cross section parallel to the air outlet is obtained: M=(360) o / (N*α)-1; Wherein, M is the number of rotations, N is the number of detection units, and α is the predetermined angle of each rotation.

Images