A method for quickly adjusting the pulsation of an aeroengine combustion chamber

Abstract

The present invention discloses a method for quickly adjusting the pulsation of an aeroengine combustion chamber, which uses a pulsation search auxiliary device. The auxiliary device includes an arcuate frame, a protective plate, an eccentric sleeve and a screw rod used in cooperation therewith, and comprises the following steps: Step 1: Install the protective plate and place the protective plate on the high-pressure turbine guide vane; Step 2: Check the initial pulsation value and find out the corresponding positions of the maximum and minimum pulsation values; Step 3: Clamp the arcuate frame on the high-pressure turbine guide vane and move it left and right to find the position where the pulsation value reaches the pulsation value required by the design drawing; Step 4: Determine the offset direction and offset amount. After determining the position where the pulsation value reaches the requirement, insert the screw rod into the screw hole at the place to be assembled of the eccentric sleeve; Step 5: Assemble the eccentric sleeve, select the eccentric sleeve for assembly according to the offset situation between the screw rod and the installation hole of the eccentric sleeve of the high-pressure turbine guide vane, take out the screw rod after the assembly is completed, and loosen the arcuate frame; Step 6: Check the pulsation value.

Description

Technical Field

[0001] The present invention belongs to the technical field of the assembly of aero-engine components, and particularly relates to a method for quickly adjusting the runout of an aero-engine combustion chamber. Background Technique

[0002] After the assembly of the aero-engine combustion chamber, it is necessary to ensure that the runout of the surface of the high-pressure turbine guide vane relative to the mounting hole of the combustion chamber casing is not greater than 0.1 mm. The design drawing requires that this runout adjustment is achieved by moving the mounting position of the high-pressure turbine guide vane relative to the combustion chamber casing, and is adjusted and fixed by selecting different groups of eccentric sleeves. However, during the assembly of the combustion chamber, it is very difficult to determine the group of the eccentric sleeve and the installation direction of the eccentric sleeve. There are a total of 8 groups of eccentric sleeves for the combustion chamber, and their eccentric amounts are in the range of 0 to 0.7. When the runout adjustment is qualified, it is necessary to determine the group of the eccentric sleeve and the installation direction of the eccentric sleeve according to the offset amount and offset direction between the mounting hole of the high-pressure turbine guide vane and the mounting screw hole of the combustion chamber, but this offset amount and offset direction cannot be determined by measurement. Therefore, the situation that it is difficult to adjust and ensure the runout requirement of the combustion chamber often occurs.

[0003] In view of this, research and improvement are carried out on the existing assembly adjustment method of the aero-engine combustion chamber, and a tool that can help quickly and accurately select the group of the eccentric sleeve and determine the installation direction of the eccentric sleeve is designed and manufactured, so as to achieve the purpose of quickly and accurately adjusting the runout of the combustion chamber. Summary of the Invention

[0004] In order to solve the above problems, the present invention aims to provide a method for quickly adjusting the runout of an aero-engine combustion chamber.

[0005] In order to achieve the above purpose, the present invention adopts the following technical solutions: A method for quickly adjusting the runout of an aero-engine combustion chamber, which uses a runout search auxiliary device. The auxiliary device includes an arch-shaped frame, a protective plate, an eccentric sleeve and a screw rod used in cooperation with it, and includes the following steps:

[0006] Step 1: Install the protective plate and place the protective plate on the high-pressure turbine guide vane.

[0007] Step 2: Check the initial runout value and find the corresponding positions of the maximum and minimum runout values.

[0008] Step 3: Clamp the arch-shaped frame on the high-pressure turbine guide vane and move it left and right to find the position where the runout value reaches the runout value required by the design drawing.

[0009] Step 4: Determine the offset direction and offset amount. After determining the position where the runout value reaches the requirement, insert the screw rod into the screw hole at the place where the eccentric sleeve is to be assembled, observe the position of the mounting hole of the high-pressure turbine guide vane eccentric sleeve and the screw rod, and determine the offset position.

[0010] Step 5: Assemble the eccentric sleeve. Select the eccentric sleeve for assembly according to the offset between the screw and the mounting hole of the eccentric sleeve of the high-pressure turbine guide. After assembly, remove the screw and loosen the bow frame.

[0011] Step 6: Check the runout value.

[0012] Preferably, the bow frame includes a left bow frame, a right bow frame and a middle part of the bow frame connected to the left and right bow frames, and a bevel transition is provided on the outer surface of the connection. The other end of the right bow frame also extends a rectangular block parallel to the middle part of the bow frame and in the same direction.

[0013] Preferably, the screw rod is a long round rod with threads at the lower end and a square upper end, and the threads at the lower end cooperate with the screw holes at the fitting position of the eccentric sleeve.

[0014] Preferably, the tool for detecting the runout value is a dial indicator.

[0015] Preferably, in step 3, according to the jitter value required by the design drawing, within the maximum / minimum value range, the position of the required jitter value is estimated, and the right bow of the bow is used to contact the high-pressure turbine guide vane and move it to the estimated position.

[0016] Preferably, in step 4, a tool is used to clamp the square surface of the upper end of the screw rod, and the threaded lower end is screwed into the screw hole of the eccentric sleeve to be assembled.

[0017] Preferably, in step 5, the offset between the screw and the eccentric sleeve mounting hole is visually observed, the eccentric sleeve is selected according to the offset, the center hole of the eccentric sleeve is inserted into the screw, and the eccentric sleeve is fixed with screws for assembly.

[0018] Preferably, in step 6, the check of the runout value is divided into two times, the first time is to check after the assembly is completed, and after the runout value is correct, the screws are tightened, and the final runout check is performed again.

[0019] Compared with the prior art, the present invention has the following advantages: through the use of the auxiliary device for beating search, the combustion chamber beating adjustment is convenient, fast and labor-saving, the eccentric sleeve group is selected accurately and conveniently, the installation direction of the eccentric sleeve is determined accurately, the combustion chamber beating amount is guaranteed, and the combustion chamber assembly efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1Schematic diagram of the pulsation adjustment of the aero-engine combustion chamber in the present invention;

[0022] In the figure, 1 - bow-shaped bracket; 2 - protective plate; 3 - eccentric sleeve; 4 - screw. Specific implementation mode

[0023] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter of the present invention is limited to the following embodiments. Without departing from the above technical ideas of the present invention, all modifications, substitutions and changes made according to ordinary technical knowledge and customary means in the art are included in the scope of the present invention.

[0024] Refer to Figure 1 , the pulsation search auxiliary device includes a bow-shaped bracket 1, a protective plate 2, an eccentric sleeve 3 and a screw 4 used in cooperation therewith. The bow-shaped bracket 1 includes a left bow-shaped bracket, a right bow-shaped bracket and a middle part of the bow-shaped bracket connected between the left and right bow-shaped brackets. There is also a bevel transition on the outer surface of the connection part. The other end of the right bow-shaped bracket also extends a rectangular block parallel and in the same direction as the middle part of the bow-shaped bracket. The screw 4 is an oblong rod with a thread at the lower end and a square shape at the upper end. The thread at the lower end is used in cooperation with the screw hole at the assembly part of the eccentric sleeve. The detection tool for the following pulsation value is a dial indicator.

[0025] A method for quickly adjusting the pulsation of an aero-engine combustion chamber includes the following steps:

[0026] Step 1: Install the protective plate 2, place the protective plate 2 on the high-pressure turbine guide vane to prevent foreign objects from entering the combustion chamber cavity and protect against part foreign objects;

[0027] Step 2: Check the initial pulsation value, find the corresponding positions of the maximum and minimum pulsation values, and facilitate determining the adjustment direction according to the pulsation positions of the maximum and minimum values;

[0028] Step 3: Clamp the bow-shaped bracket 1 on the high-pressure turbine guide vane. The design requirement is that the pulsation of the surface of the high-pressure turbine guide vane relative to the installation hole of the combustion chamber casing is not greater than 0.1 mm. According to the required pulsation value, estimate the position with a pulsation value not greater than 0.1 mm within the maximum / minimum value range. Use the right bow-shaped bracket of the bow-shaped bracket 1 to contact the high-pressure turbine guide vane and move it to the position with a pulsation value not greater than 0.1 mm;

[0029] Step 4: Determine the offset direction and offset amount. After determining the position where the pulsation value reaches not greater than 0.1 mm, insert the screw 4 into the screw hole at the assembly part of the eccentric sleeve 3 to determine the position; use a wrench to clamp the square surface at the upper end of the screw 4 and screw the threaded lower end into the screw hole at the assembly part of the eccentric sleeve;

[0030] Step 5: Assemble the eccentric sleeve 3, visually check the offset of the screw rod 4 and the mounting hole of the eccentric sleeve 3, select the eccentric sleeve 3 according to the offset situation, insert the central hole of the eccentric sleeve 3 into the screw rod 4, and fix the eccentric sleeve 3 with screws for assembly. After the assembly is completed, take out the screw rod 4 and loosen the bow-shaped frame 1;

[0031] Step 6: Check the runout value. The check of the runout value is divided into two times. The first time is to conduct the detection after the assembly is completed. After the runout value is correct, tighten the screws, and then conduct the final runout detection again, which ensures the runout of the combustion chamber and improves the assembly efficiency of the combustion chamber.

[0032] The above has introduced in detail a method for quickly adjusting the runout of an aero-engine combustion chamber provided by the present invention. Specific examples are used in this article to elaborate on the structure and working principle of the present invention. The description of the above embodiments is only used to help understand the method and core idea of the present invention. It should be noted that for those of ordinary skill in the art of this technology, without departing from the principle of the present invention, several improvements and modifications can still be made to the present invention, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A method for quickly adjusting the pulsation of an aeroengine combustion chamber, characterized in that: Adopt a beating search auxiliary device. The auxiliary device includes an arch frame (1), a protective plate (2), an eccentric sleeve (3) and a screw rod (4) used in cooperation therewith, and includes the following steps: Step 1: Install the protective plate (2) and place the protective plate (2) on the high-pressure turbine guide vane; Step 2: Check the initial beating value and find the corresponding positions of the maximum and minimum beating values; Step 3: Clamp the arch frame (1) on the high-pressure turbine guide vane and move it left and right to find the position where the beating value reaches the beating value required by the design drawing. Step 4: Determine the offset direction and offset amount. After determining the position where the beating value reaches the requirement, insert the screw rod (4) into the screw hole at the place to be assembled of the eccentric sleeve (3), observe the position of the eccentric sleeve mounting hole of the high-pressure turbine guide vane and the screw rod (4), and determine the offset position; Step 5: Assemble the eccentric sleeve (3). Select the eccentric sleeve (3) for assembly according to the offset situation between the screw rod (4) and the eccentric sleeve mounting hole of the high-pressure turbine guide vane. After assembly, take out the screw rod (4) and loosen the arch frame (1); Step 6: Check the beating value.

2. The method for quickly adjusting the pulsation of an aeroengine combustor according to claim 1, characterized in that: The arch frame (1) includes a left arch frame, a right arch frame and an arch frame middle part connecting the left and right arch frames. There is also a chamfer transition on the outer surface at the connection. The other end of the right arch frame also extends a rectangular block parallel to and in the same direction as the arch frame middle part.

3. The method for quickly adjusting the pulsation of an aeroengine combustor according to claim 1, characterized in that: The screw rod (4) is an oval rod with a thread at the lower end and a square shape at the upper end. The thread at the lower end is used in cooperation with the screw hole at the place to be assembled of the eccentric sleeve.

4. The method for quickly adjusting the pulsation of an aeroengine combustion chamber according to claim 1, characterized in that: The detection tool for the beating value is a dial indicator.

5. The method for quickly adjusting the pulsation of an aeroengine combustion chamber according to claim 2, characterized in that: In Step 3, according to the beating value required by the design drawing, estimate the position of the required beating value within the maximum / minimum value range, make the right arch frame of the arch frame (1) contact the high-pressure turbine guide vane and move it to the estimated position.

6. The method for quickly adjusting the pulsation of an aero-engine combustion chamber according to claim 3, characterized in that: In Step 4, use a tool to clamp the square surface at the upper end of the screw rod (4) and screw the threaded lower end into the screw hole at the place to be assembled of the eccentric sleeve.

7. The method for quickly adjusting the pulsation of an aeroengine combustion chamber according to claim 1, characterized in that: In Step 5, visually observe the offset situation between the screw rod (4) and the mounting hole of the eccentric sleeve (3), select the eccentric sleeve (3) according to the offset situation, put the central hole of the eccentric sleeve (3) on the screw rod (4), and fix the eccentric sleeve (3) with screws for assembly.

8. The method for quickly adjusting the pulsation of an aeroengine combustor according to claim 1, characterized in that: In Step 6, the inspection of the beating value is carried out twice. The first time is to detect after the assembly is completed. After the beating value is correct, tighten the screw, and then conduct the final beating detection again.

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