Combustion chamber flange assembly, design checking method thereof and aero-engine combustion chamber

Abstract

The invention relates to a combustion chamber flange assembly, a design checking method of the combustion chamber flange assembly and an aero-engine combustion chamber, and the combustion chamber flange assembly comprises a first flange and a second flange, the second flange is in butt joint with the first flange, a protruding part is arranged on the butt joint face in the circumferential direction, the size of the protruding part in the radial direction is larger than the width of the containing groove in the radial direction, and the protruding part covers the containing groove and abuts against the butt joint plane of the first flange; the fastening piece is connected between the first flange and the second flange in the axial direction, and the containing groove and the protruding part are both located on the radial inner side of the fastening piece; the sealing ring is arranged in the containing groove, the sealing ring abuts against the position between the bottom face of the containing groove and the top face of the protruding part in the axial direction, the sealing ring is in a compressed state, the tolerable temperature of the sealing ring is larger than the working temperature of the combustion chamber, and the tolerable pressure of the sealing ring is larger than the inner cavity pressure of the combustion chamber.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine combustors, and in particular to a combustor flange assembly and its design verification method, and an aero-engine combustor. Background Technology

[0002] Currently, the development of combustion chamber components for aero-engines typically employs single-sector and full-ring test specimens to support component design determination and verify the performance of the test scheme. Because the internal pressure of the test specimen casing is relatively high, typically 3MPa to 4MPa, and the temperature is also high, around 700℃, a sealing structure needs to be designed between the flanges connecting the casing to prevent leakage of high-temperature, high-pressure gases. Currently, the commonly used sealing method is the tongue and groove gasket type, but the sealing effect is not ideal, and leakage occurs during testing. A large amount of high-temperature, high-pressure white gas leaks between the flanges, posing a safety hazard and affecting the accuracy of the test gas distribution. Summary of the Invention

[0003] The embodiments of this disclosure provide a combustion chamber flange assembly and its design verification method, as well as an aero-engine combustion chamber, which can improve the sealing effect of the combustion chamber flange assembly.

[0004] According to a first aspect of this disclosure, a combustion chamber flange assembly is provided, comprising:

[0005] The first flange has a receiving groove along the circumferential direction on its mating surface;

[0006] The second flange is mated with the first flange, and a protrusion is provided on the mating surface along the circumferential direction. The radial dimension of the protrusion is greater than the radial width of the receiving groove. The protrusion covers the receiving groove and abuts against the mating plane of the first flange.

[0007] A fastener, axially connected between a first flange and a second flange, wherein both the receiving groove and the protrusion are located radially inside the fastener; and

[0008] The sealing ring is located in the receiving groove. The sealing ring abuts axially between the bottom surface of the receiving groove and the top surface of the protrusion and is in a compressed state. The sealing ring has a temperature resistance greater than the working temperature of the combustion chamber and a pressure resistance greater than the internal pressure of the combustion chamber.

[0009] In some embodiments, the sealing ring is made of a nickel-based high-temperature alloy.

[0010] In some embodiments, the sealing ring is a C-type sealing ring or a W-type sealing ring.

[0011] In some embodiments, the sealing ring is a C-shaped sealing ring with the opening facing radially inward and the C-shaped sealing ring abutting axially between the bottom surface of the receiving groove and the top surface of the protrusion.

[0012] In some embodiments, the radial width of the receiving groove is greater than or equal to the radial dimension of the C-type seal in the compressed state.

[0013] In some embodiments, the radial distance between the receiving groove and the fastener is less than a preset distance.

[0014] According to a second aspect of this disclosure, an aircraft engine combustion chamber is provided, including the combustion chamber flange assembly of the above embodiments.

[0015] According to a third aspect of this disclosure, a design verification method for a combustion chamber flange assembly is provided, used for designing and verifying the combustion chamber flange assembly of the above embodiments. The design verification method for the combustion chamber flange assembly includes:

[0016] Select the material of the sealing ring according to the operating temperature of the combustion chamber;

[0017] Select the appropriate sealing ring model based on the size of the receiving groove;

[0018] Select the sealing ring model according to the internal pressure of the combustion chamber;

[0019] Perform a seal check on the sealing ring at room temperature;

[0020] Perform a seal check on the sealing ring at the operating temperature.

[0021] In some embodiments, the sealing ring is a C-type sealing ring, and the receiving groove, the protrusion, and the sealing ring are all annular. The model of the sealing ring selected according to the size of the receiving groove includes:

[0022] Select the matching C-type sealing ring cross-sectional dimensions based on the outer diameter of the receiving groove. The C-type sealing ring cross-sectional dimensions include the outer diameter, wall thickness, and notch size.

[0023] In some embodiments, performing a sealing check on the sealing ring at room temperature includes:

[0024] Calculate the first clamping force required for the C-type sealing ring to meet the sealing requirements based on the circumferential length of the C-type sealing ring;

[0025] Calculate the second clamping force provided by the fasteners based on their size and quantity;

[0026] If the second clamping force is greater than the first clamping force, the verification is passed. If the second clamping force is not greater than the first clamping force, the model of the sealing ring is reselected, or the size or quantity of the fasteners is reselected.

[0027] In some embodiments, performing a seal check on the sealing ring at the operating temperature includes:

[0028] The maximum deformation of the C-type sealing ring at the operating temperature was calculated based on finite element analysis.

[0029] The rebound amount of the C-type seal is determined according to the seal type.

[0030] If the springback is greater than the maximum deformation, the seal ring model should be re-selected. If the springback is not greater than the maximum deformation, the seal ring model should be re-selected.

[0031] Based on the above technical solution, the combustion chamber flange assembly of this disclosure, by setting a sealing ring in the receiving groove and having the sealing ring in a compressed state, can ensure that the sealing ring is always axially abutting between the bottom surface of the receiving groove and the top surface of the protrusion in both the non-working state and the high-temperature and high-pressure working state. This can improve the sealing effect of the combustion chamber flange assembly, maintain the sealing performance of the combustion chamber in the working state, prevent the leakage of high-temperature and high-pressure gas between the flanges, and improve the safety of the combustion chamber and the accuracy of the combustion chamber gas distribution. Attached Figure Description

[0032] The accompanying drawings, which are included to provide a further understanding of this disclosure and form part of this disclosure, illustrate exemplary embodiments of the present disclosure and are used to explain the disclosure, but do not constitute an undue limitation of the disclosure. In the drawings:

[0033] Figure 1 This is a schematic diagram of the structure of some embodiments of the combustion chamber flange assembly disclosed herein.

[0034] Figure 2 This is an enlarged schematic diagram of some embodiments of the combustion chamber flange assembly disclosed herein.

[0035] Figure 3 This is a structural schematic diagram of some embodiments of the first flange and sealing ring of the combustion chamber flange assembly disclosed herein.

[0036] Figure 4 This is a flowchart illustrating some embodiments of the combustion chamber flange assembly design verification method disclosed herein.

[0037] Explanation of reference numerals in the attached figures

[0038] 1. First flange; 2. Second flange; 3. Fastener; 4. Sealing ring; 5. Nut; 11. Receiving groove; 21. Protrusion; x, radial; y, axial. Detailed Implementation

[0039] The present disclosure is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. The aspects so defined may be combined with any other aspect or aspects unless expressly stated otherwise. In particular, any feature considered preferred or advantageous may be combined with one or more other features considered preferred or advantageous.

[0040] The terms "first" and "second" used in this disclosure are merely for ease of description and to distinguish different components with the same name, and do not indicate a sequential or primary / secondary relationship.

[0041] In the description of this disclosure, it should be understood that the terms “inner,” “outer,” “upper,” “lower,” “radial,” or “axial,” etc., indicating orientation or positional relationship, are defined based on flanges, receiving tanks, or combustion chambers, etc., and are only for the convenience of describing this disclosure, and are not intended to indicate or imply that the device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this disclosure.

[0042] First, this disclosure proposes a combustion chamber flange assembly, such as Figures 1 to 3 As shown, the combustion chamber flange assembly includes:

[0043] The first flange 1 has a circumferentially oriented receiving groove 11 on its mating surface;

[0044] The second flange 2 is mated with the first flange 1, and a protrusion 21 is provided on the mating surface along the circumferential direction. The size of the protrusion 21 along the radial x direction is greater than the width of the receiving groove 11 along the radial x direction. The protrusion 21 covers the receiving groove 11 and abuts against the mating plane of the first flange 1.

[0045] Fastener 3 is connected axially (y) between the first flange 1 and the second flange 2, with the receiving groove 11 and the protrusion 21 both located radially (x) inside the fastener 3; and

[0046] The sealing ring 4 is located in the receiving groove 11. The sealing ring 4 abuts against the bottom surface of the receiving groove 11 and the top surface of the protrusion 21 along the axial direction y and the sealing ring 4 is in a compressed state. The temperature resistance of the sealing ring 4 is greater than the working temperature of the combustion chamber, and the pressure resistance of the sealing ring 4 is greater than the internal pressure of the combustion chamber.

[0047] Specifically, the protrusion 21 completely covers the receiving groove 11, ensuring that the sealing ring 4 always abuts against the top surface of the protrusion 21 under any operating condition. Specifically, the sealing ring 4 in a compressed state applies an elastic force along the axial direction y to both the bottom surface of the receiving groove 11 and the top surface of the protrusion 21, ensuring that the sealing ring 4 can still abut against the top surface of the protrusion 21 under combustion conditions.

[0048] Specifically, during the assembly process, the protrusion 21 abuts against the mating plane of the first flange 1. However, under high temperature and high pressure, the protrusion 21 may be spaced apart from the mating plane along the axial direction y. At this time, the sealing ring 4, which is in a compressed state, rebounds, so that the sealing ring 4 continues to abut against the top surface of the protrusion 21, which can form a tight line seal on the mating ring surface, adapt to the small displacement between the flange mating planes, so as to improve the sealing effect of the combustion chamber flange and prevent a large amount of high temperature and high pressure white gas from leaking between the flanges.

[0049] Specifically, the material of sealing ring 4 is capable of withstanding the working temperature and pressure of the combustion chamber, such as high-temperature alloys or other materials with high thermal stability. Specifically, after installation, sealing ring 4 should meet the sealing requirements at both room temperature and working temperature to achieve a better sealing effect. Specifically, the working pressure can be 3MPa to 4MPa, and the working temperature is approximately 700℃.

[0050] Optionally, the receiving groove 11 can be a tenon or similar groove. Optionally, the profile of the circumferential sealing structure can be determined according to the shape of the first flange 1 and the second flange 2, for example, it can be an annular shape, a polygonal annular shape, or other arbitrary shapes. Optionally, in the radial direction, the sealing ring 4 can abut against the upper and lower sidewalls of the receiving groove 11, or it can be spaced at a predetermined distance from the upper and lower sidewalls of the receiving groove 11. Optionally, the combustion chamber can include a fuel engine combustion chamber, an aircraft engine combustion chamber, or a combustion chamber test piece, etc.

[0051] Optionally, the fastener 3 may be a bolt, and the combustion chamber flange assembly may also include a nut 5, which has a threaded hole that mates with the fastener; alternatively, the combustion chamber flange assembly may not include the nut 5, for example, one flange may have a through hole for the fastener 3 to pass through, and the other flange may have a threaded hole that mates with the fastener.

[0052] The combustion chamber flange assembly of this embodiment, by providing a sealing ring 4 in the receiving groove 11 and having the sealing ring 4 in a compressed state, can ensure that the sealing ring 4 always abuts against the bottom surface of the receiving groove 11 and the top surface of the protrusion 21 along the axial direction y at all times in both the non-working state and the high temperature and high pressure working state. This can improve the sealing effect of the combustion chamber flange assembly, maintain the sealing performance of the combustion chamber in the working state, prevent the leakage of high temperature and high pressure gas between the flanges, and improve the safety of the combustion chamber and the accuracy of the combustion chamber gas distribution.

[0053] In some embodiments, the sealing ring 4 is made of a nickel-based high-temperature alloy.

[0054] Specifically, the material of sealing ring 4 can be Waspaloy, a high-performance nickel-based superheat-resistant alloy mainly used in the manufacture of high-temperature components in the aerospace industry, such as gas turbine blades, discs, shafts, and fasteners. Waspaloy's main components include nickel, chromium, cobalt, molybdenum, aluminum, titanium, and trace amounts of niobium and boron. Due to its excellent creep resistance, oxidation resistance, and fatigue resistance, it maintains good sealing performance even in high-temperature environments.

[0055] This embodiment improves the resistance of the sealing ring 4 to high temperature and high pressure environments by selecting nickel-based high-temperature alloy as the material of the sealing ring 4, thereby improving the sealing effect of the combustion chamber flange and maintaining the sealing performance of the combustion chamber under working conditions.

[0056] In some embodiments, the sealing ring 4 is a C-type sealing ring or a W-type sealing ring.

[0057] Specifically, C-type or W-type sealing rings are not made of materials such as rubber or silicone, but rather of materials that can withstand high temperatures and pressures. In comparison, C-type sealing rings are simpler to manufacture, have slightly higher pressure loads, and slightly weaker deformation compensation capabilities, while W-type sealing rings have slightly lower pressure loads and slightly stronger deformation compensation capabilities. Operators can choose the appropriate type based on actual working conditions.

[0058] This embodiment, by employing a C-type or W-type sealing ring, can prevent medium leakage from the combustion chamber through its own sealing cross-section and compression, thereby improving the sealing effect of the combustion chamber flange and maintaining the sealing performance of the combustion chamber under operating conditions.

[0059] In some embodiments, such as Figure 1 and Figure 2 As shown, the sealing ring 4 is a C-type sealing ring. The opening of the C-type sealing ring faces the radial x-inward side, and the C-type sealing ring abuts against the bottom surface of the receiving groove 11 and the top surface of the protrusion 21 along the axial y-axis.

[0060] Specifically, the opening of the C-type sealing ring faces radially inward. During flange assembly, axial compression causes the two sides of the C-type sealing ring to fit more tightly against the bottom surface of the receiving groove 11 and the top surface of the opposite protrusion 21. This arrangement enhances the reliability of the C-type sealing ring under pressure conditions.

[0061] This embodiment, by oriented the opening of the C-type sealing ring towards the radial x-inward side, can utilize the structural characteristics of the C-type sealing ring to provide optimal sealing performance, improve the pressure resistance of the sealing ring, and meet the stringent sealing requirements of the combustion chamber flange assembly under high temperature and high pressure conditions.

[0062] In some embodiments, such as Figure 1 and Figure 2As shown, the width of the receiving groove 11 along the radial x direction is greater than or equal to the radial x dimension of the C-type sealing ring under compression.

[0063] Optionally, the width of the receiving groove 11 along the radial x direction can be greater than or equal to the radial x direction of the C-type sealing ring under compressed conditions.

[0064] This embodiment provides space for the deformation of the C-type sealing ring by making the width of the receiving groove 11 along the radial x direction greater than or equal to the size of the C-type sealing ring along the radial x direction under compression. This helps to ensure that the deformation of the C-type sealing ring meets the sealing requirements under working conditions.

[0065] In some embodiments, the radial distance between the receiving groove 11 and the fastener 3 is less than a preset distance.

[0066] Specifically, by minimizing the radial distance between the receiving groove 11 and the fastener 3, the lever arm length can be reduced, allowing the preload applied by the fastener 3 to be applied as much as possible between the receiving groove 11 and the protrusion 21. This reduces the likelihood of minor displacement between the mating surfaces, thereby achieving a better sealing effect when combined with the sealing ring 4. Optionally, the preset distance can be set according to engineering manuals, corporate standards, or employee experience.

[0067] This embodiment reduces the radial distance between the receiving groove 11 and the fastener 3, thereby reducing the lever arm length, improving the sealing effect of the combustion chamber flange assembly, and maintaining the sealing performance of the combustion chamber in operation.

[0068] Secondly, this disclosure proposes an aero-engine combustion chamber, including the combustion chamber flange assembly of the above embodiments.

[0069] Optionally, the aero-engine combustor includes an aero-engine combustor test piece. By improving the flange sealing effect at the operating temperature, leakage during the test can be avoided, preventing the leakage of a large amount of high-temperature and high-pressure white gas between the flanges. This can improve the safety of the aero-engine combustor test and improve the accuracy of the test gas distribution.

[0070] The combustion chamber of the aircraft engine in this embodiment has a good sealing effect of the combustion chamber flange assembly, which makes the aircraft engine combustion chamber well sealed in the working state, and can prevent the leakage of high temperature and high pressure gas from the aircraft engine combustion chamber, thereby improving the safety of the aircraft engine combustion chamber and the accuracy of the gas volume distribution in the aircraft engine combustion chamber.

[0071] Furthermore, this disclosure also proposes a design verification method for a combustion chamber flange assembly, used for designing and verifying the combustion chamber flange assembly of the above embodiments, such as... Figure 4 As shown, the design verification method for the combustion chamber flange assembly includes:

[0072] The material of sealing ring 4 should be selected according to the operating temperature of the combustion chamber;

[0073] Select the appropriate sealing ring 4 model based on the dimensions of the receiving groove 11;

[0074] Select the model of sealing ring 4 according to the internal pressure of the combustion chamber;

[0075] Perform a sealing check on sealing ring 4 at room temperature;

[0076] Perform a seal check on sealing ring 4 at the operating temperature.

[0077] Specifically, the sealing ring 4 needs to be made of a material capable of withstanding the high temperature and pressure during combustion chamber operation. The size and model of the sealing ring 4 must precisely match the size of the receiving groove 11 to ensure that the sealing ring 4 forms an effective seal under compression. Specifically, a seal check at room temperature ensures the sealing effectiveness of the sealing ring 4 at room temperature, while a seal check at operating temperature ensures the sealing effectiveness of the sealing ring 4 at operating temperature. Specifically, if the C-type sealing ring can meet all the above sealing requirements at both room temperature and operating temperature (high temperature), it indicates that under actual operating conditions, no gas leakage between the flanges can be ensured.

[0078] Specifically, selecting the model of sealing ring 4 based on the internal pressure of the combustion chamber ensures that sealing ring 4 can withstand the internal pressure of the high-pressure vessel. Specifically, the physical properties of sealing ring 4 (such as elasticity and hardness) may change at operating temperatures, affecting its sealing performance. Optionally, the sealing performance of sealing ring 4 at operating temperatures can be verified using simulation software such as finite element analysis (FEA).

[0079] The combustion chamber flange assembly design verification method of this embodiment, by selecting and verifying the sealing ring 4, can ensure that the material, model and size of the sealing ring 4, the sealing performance at room temperature and the sealing performance at working pressure all meet the sealing requirements, thereby improving the sealing effect of the combustion chamber flange assembly, improving the safety of the combustion chamber and the accuracy of the combustion chamber gas distribution.

[0080] In some embodiments, the sealing ring 4 is a C-shaped sealing ring, and the receiving groove 11, the protrusion 21, and the sealing ring 4 are all annular. The model of the sealing ring 4 that matches the size of the receiving groove 11 includes:

[0081] Select the matching C-type sealing ring cross-sectional dimensions based on the outer diameter of the receiving groove 11. The C-type sealing ring cross-sectional dimensions include the outer diameter, wall thickness, and notch size.

[0082] Select the C-type sealing ring with the corresponding section code based on the pre-selected outer diameter D of the sealing groove.

[0083] This embodiment ensures that the C-type sealing ring model is precisely matched with the outer diameter of the receiving groove 11 by selecting the cross-sectional size of the C-type sealing ring according to the outer diameter of the receiving groove, so as to achieve a better sealing effect.

[0084] In some embodiments, performing a sealing check on the sealing ring 4 at room temperature includes:

[0085] Calculate the first clamping force required for the C-type sealing ring to meet the sealing requirements based on the circumferential length of the C-type sealing ring;

[0086] The second clamping force provided by fastener 3 is calculated based on the size and quantity of fastener 3;

[0087] If the second clamping force is greater than the first clamping force, the verification is passed. If the second clamping force is not greater than the first clamping force, the model of the sealing ring 4 is reselected, or the size or quantity of the fastener 3 is reselected.

[0088] Specifically, the first clamping force required for the C-type sealing ring to meet the sealing requirements can be calculated by the formula Wx=L*F', where Wx is the first clamping force, L is the circumference of the C-type sealing ring, and F' is the clamping force required per millimeter of length, which can be found in the C-type sealing ring enterprise standard.

[0089] Specifically, when fastener 3 is a bolt, the second clamping force provided by fastener 3 can be calculated by the formula Ws=T / K / d*N, where Ws is the second clamping force, T is the tightening torque value obtained from the standard HB 6586-1992 based on the nominal diameter and bolt material of the bolt, K is the torque coefficient, which can be obtained from the standard and is usually taken as 0.2, d is the selected bolt diameter, and N is the number of bolts. d and N are initially selected based on experimental experience, etc. If the sealing requirements are not met, the values ​​of d and N are changed and rechecked.

[0090] Specifically, if Ws>Wx, it indicates that the second preload applied by fastener 3 is greater than the first clamping force required for the C-type sealing ring to seal, which can meet the sealing requirements; otherwise, the specification code of the C-type sealing ring needs to be reselected and rechecked.

[0091] The design verification method of this embodiment compares the second clamping force that the fastener 3 can provide with the first clamping force required for the C-type sealing ring to meet the sealing requirements, and performs a sealing verification of the C-type sealing ring at room temperature, which can improve the sealing effect of the combustion chamber flange assembly.

[0092] In some embodiments, performing a seal check on the sealing ring 4 at the operating temperature includes:

[0093] The maximum deformation of the C-type sealing ring at the operating temperature was calculated based on finite element analysis.

[0094] The rebound amount of the C-type sealing ring is determined according to the model of sealing ring 4;

[0095] If the rebound amount is greater than the maximum deformation amount, the model of sealing ring 4 is reselected.

[0096] Specifically, at the operating temperature, the maximum deformation Ss at the C-type seal is calculated using finite element analysis. The rebound amount Sx of the C-type seal is then found in the enterprise standard for the C-type seal according to the corresponding section code. If Sx > Ss, the sealing requirements under operating conditions are met; otherwise, the specification code of the C-type seal needs to be reselected and the verification is repeated.

[0097] The design verification method of this embodiment combines finite element analysis to calculate the deformation amount and compare it with the rebound amount, which can verify the sealing of the C-type sealing ring at the working temperature and further improve the sealing effect of the combustion chamber flange assembly.

[0098] The foregoing has provided a detailed description of a combustion chamber flange assembly and its design verification method, as well as an aero-engine combustion chamber. Specific embodiments have been used to illustrate the principles and implementation methods of this disclosure. These embodiments are merely illustrative and are intended to aid in understanding the method and core concepts of this disclosure. It should be noted that those skilled in the art can make various improvements and modifications to this disclosure without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of this disclosure.

Claims

1. A combustion chamber flange assembly characterized by, The application relates to a combustion chamber flange assembly, comprising: a first flange (1) provided with a receiving groove (11) on the abutting surface in the circumferential direction; a second flange (2) abutting with the first flange (1) and provided with a protrusion (21) on the abutting surface in the circumferential direction, the protrusion (21) has a dimension along the radial direction (x) which is greater than the width of the receiving groove (11) along the radial direction (x), the protrusion (21) covers the receiving groove (11) and abuts against the abutting surface of the first flange (1); a fastener (3) connected between the first flange (1) and the second flange (2) along the axial direction (y), the receiving groove (11) and the protrusion (21) are located inside the radial direction (x) of the fastener (3); and a sealing ring (4) arranged in the receiving groove (11), the sealing ring (4) abuts between the bottom surface of the receiving groove (11) and the top surface of the protrusion (21) along the axial direction (y) and is in a compressed state, the sealing ring (4) has a temperature resistance greater than the working temperature of the combustion chamber, and the sealing ring (4) has a pressure resistance greater than the internal cavity pressure of the combustion chamber.

2. The combustion chamber flange assembly of claim 1, wherein, The material of the sealing ring (4) is a nickel-based high-temperature alloy.

3. The combustion chamber flange assembly of claim 1, wherein, The sealing ring (4) is a C-shaped sealing ring or a W-shaped sealing ring.

4. The combustion chamber flange assembly of claim 1, wherein, The sealing ring (4) is a C-shaped sealing ring, the opening of the C-shaped sealing ring faces the inside of the radial direction (x), and the C-shaped sealing ring abuts between the bottom surface of the receiving groove (11) and the top surface of the protrusion (21) along the axial direction (y).

5. The combustion chamber flange assembly of claim 4, wherein, The width of the receiving groove (11) along the radial direction (x) is greater than or equal to the dimension of the C-shaped sealing ring along the radial direction (x) in a compressed state.

6. The combustion chamber flange assembly of claim 1, wherein, The radial distance between the receiving groove (11) and the fastener (3) is less than a preset distance.

7. An aircraft engine combustion chamber characterized by, The application further discloses a combustion chamber flange assembly comprising any one of the combustion chamber flange assemblies in claims 1-6.

8. A method of designing and checking a combustion chamber flange assembly, characterized in that, The application further discloses a design and check method of the combustion chamber flange assembly in any one of claims 1-6, and the design and check method comprises: selecting the material of the sealing ring (4) according to the working temperature of the combustion chamber; selecting the type of the sealing ring (4) according to the size of the receiving groove (11); selecting the type of the sealing ring (4) according to the internal cavity pressure of the combustion chamber; performing sealing check on the sealing ring (4) at room temperature; performing sealing check on the sealing ring (4) at the working temperature.

9. The combustion chamber flange assembly design review method of claim 8, wherein, The sealing ring (4) is a C-shaped sealing ring, the receiving groove (11), the protrusion (21) and the sealing ring (4) are all annular, and selecting the type of the sealing ring (4) according to the size of the receiving groove (11) comprises: selecting the cross-sectional size of the C-shaped sealing ring according to the outer diameter size of the receiving groove (11), the cross-sectional size of the C-shaped sealing ring comprises the cross-sectional outer diameter, the wall thickness and the notch size.

10. The combustion chamber flange assembly design review method of claim 9, wherein, Performing sealing check on the sealing ring (4) at room temperature comprises: calculating the first pressing force required for the C-shaped sealing ring to meet the sealing requirement according to the circumferential length of the C-shaped sealing ring; calculating a second compression force provided by the fasteners (3) according to the size and number of the fasteners (3); in the case where the second compression force is greater than the first compression force, checking, in the case where the second compression force is not greater than the first compression force, reselecting the type of the sealing ring (4), or reselecting the size or number of the fasteners (3).

11. The combustion chamber flange assembly design review method of claim 9 or 10, wherein, the sealing check of the sealing ring (4) at the working temperature comprises: calculating a maximum deformation amount of the C-shaped sealing ring at the working temperature according to the finite element analysis; determining a rebound amount of the C-shaped sealing ring according to the type of the sealing ring (4); in the case where the rebound amount is greater than the maximum deformation amount, checking, in the case where the rebound amount is not greater than the maximum deformation amount, reselecting the type of the sealing ring (4).

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