CN112507456A - Method for designing parameters of reusable rocket engine thrust chamber cooling groove - Google Patents
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Abstract
The application relates to the technical field of aerospace, in particular to a parameter design method for a reusable rocket engine thrust chamber cooling groove. The parameter design method for the reusable rocket engine thrust chamber cooling groove comprises the following steps: presetting the service life of the cooling tank as N; calculating the thinning limit times of the thrust chamber wall material to be NT(ii) a Mixing N with NTCarrying out comparison; when N is present<NTIf the stretching is unstable and invalid, designing parameters according to a calculation method of the stretching unstable and invalid; when N is present>NTAnd if the fatigue failure is indicated, designing parameters according to a calculation method of the fatigue failure. According to the method and the device, the cooling tank parameters are calculated according to the given service life, and the calculation process is simple, convenient and effective without any simulation calculation process.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a parameter design method for a reusable rocket engine thrust chamber cooling groove.
Background
In the existing parameter design of the reusable rocket engine thrust chamber cooling tank, the general range of the parameters is generally determined according to experience after the expected target performance and service life requirements are given, one group of parameters is selected for design, then the service life is calculated, whether the conditions can be met or not is judged, if not, the service life is calculated again after redesign is needed, and the steps are repeated.
In the aspect of calculating the service life of the cooling groove of the thrust chamber, a common finite element simulation calculation method needs a large amount of calculation; the other method is that the method uses the classical plasticity theory calculation, has complex steps and needs to combine with simulation results, and is difficult to be used in engineering practice.
At present, the design method for checking the service life after designing parameters is complex in process, and due to numerous parameter combinations, an expected service life result cannot be obtained.
Disclosure of Invention
The application aims to provide a method for designing parameters of a reusable rocket engine thrust chamber cooling groove, and solves the technical problem that the design method for designing parameters and checking the service life is complex in process in the prior art to a certain extent.
The application provides a method for designing parameters of a reusable rocket engine thrust chamber cooling groove, which comprises the following steps:
presetting the service life of the cooling tank as N;
calculating the thinning limit times of the thrust chamber wall material to be NT；
Mixing N with NTCarrying out comparison;
when N is present<NTIf the stretching is unstable and invalid, designing parameters according to a calculation method of the stretching unstable and invalid; when N is present>NTAnd if the fatigue failure is indicated, designing parameters according to a calculation method of the fatigue failure.
In the above technical solution, further, the limit number N of thinning of the inner wall of the thrust chamber is calculatedTCalculated by the formula (1)：
NT＝750n1.25 (1)
Wherein,
wherein s isuIs the ultimate strength (Pa) of the material; syThe material yield strength (Pa).
In the above technical solution, further, when N is greater than N<NTIf the tensile instability failure is indicated, the parameter design according to the calculation method of the tensile instability failure comprises the following steps:
obtaining the temperatures of the gas side inner wall and the coolant side inner wall of the cooling tank as T2、T3；
According to T2And T3Determining the axial inelastic strain delta epsilon 'caused by the different coefficients of thermal expansion of the inner and outer walls of the cooling slot'p1And axial strain Delta epsilon caused by thermal stress of the cooling groove "p1And is according to Δ ε'p1And. DELTA. epsilon "p1Determination of the axial strain Deltaepsilon of the cooling channelp1；
According to the axial strain Delta epsilon of the cooling groovep1Determining the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2And according to the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2Determining the total deformation delta of the inner wall of the cooling tank;
and determining a functional relation which is satisfied between the service life N of the cooling tank and the parameters H, L and W when the stretching instability fails according to the total deformation delta of the inner wall of the cooling tank.
In the above technical solution, further, the step of calculating the temperatures of the gas side inner wall and the coolant side inner wall of the cooling tank as T respectively2、T3The method comprises the following steps:
t can be obtained by a one-dimensional heat transfer calculation formula of the thrust chamber2The one-dimensional heat transfer calculation of the thrust chamber is shown as a formula (2):
wherein,
wherein,
calculating T according to the formula (3)3：
Wherein,
wherein k is the thermal conductivity, T4Is the coolant temperature, T1Is the gas temperature, h is the cooling channel height, Ma is the Mach number, mu is the gas viscosity, DtIs the throat diameter, prIs the prandtl number of the coolant, cpFor gas mean mass constant pressure heat capacity, pcIs the combustion chamber pressure, c*For characteristic velocity, R is the throat radius of curvature, AtIs the throat area, A is the axial cross-sectional area, gamma is the specific heat ratio of the fuel gas, h1Is the convective heat transfer coefficient; re is Reynolds number, prwIs the Prandtl number, lambda, of the coolant at the wallfIs the heat conductivity of the coolant, deIs the hydraulic diameter.
In the above technical solution, further, the axial strain Δ ∈ of the cooling groovep1And calculating according to the formula (4) to obtain:
wherein alpha is the coefficient of thermal expansion of the inner wall, v is the Poisson's ratio, E is the elastic modulus of the inner wall,
is constant and equal to 0.35.
In the above technical solution, further, the axial strain Δ ∈ according to the cooling groove is measuredp1Determining the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2And according to the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2Determining the total deformation delta of the inner wall of the cooling tank, and calculating according to a formula (5):
h is the thickness of the inner wall of the cooling groove, L is the width of a cooling channel of the cooling groove, and W is the thickness of a ribbed plate of the cooling groove.
In the above technical solution, further, when determining that the stretching is unstable and fails according to the total deformation δ of the inner wall of the cooling tank, the step of calculating the functional relationship satisfied between the service life N of the cooling tank and the parameters H, L and W is as follows:
the expression for determining the service life N of the cooling tank according to the deformation failure of the cooling tank is shown in the formula (6):
wherein e is a constant;
substituting the formula (5) into the formula (6) to obtain the formula (7):
in the above technical solution, further, when N is greater than N>NTIf the fatigue failure is indicated, the parameter design according to the fatigue failure calculation method comprises the following steps:
the relation for determining the fatigue life parameter is shown as the formula (8):
wherein,
represents the minimum cross-sectional effective strain, NFB and c are constants related to material characteristics, namely the fatigue life of the thrust chamber;
from the plastic deformation formula, the minimum cross section has an effect as shown in formula (9):
wherein epsilon1minAnd ε2minRespectively representing the radial minimum section strain and the axial minimum section strain, epsilon1minAs shown in equation (10), ε2minAs shown in formula (11):
wherein epsilon1avg＝ε2min，
Order to
Namely, the relation of fatigue life parameters is obtained as shown in the formula (12):
in the above technical solution, further, substituting the parameter obtained by equation (12) into equation (7) obtains a result greater than NT。
In the above technical solution, further, when the wall material in the thrust chamber is Narloy-Z, b is 0.549, and c is-0.4844; when the material of the inner wall of the thrust chamber is the OFHC function, b is 0.1669, and c is-0.44.
Compared with the prior art, the beneficial effect of this application is:
the application provides a reusable rocket engine thrust chamber cooling groove parameter design method, which comprises the following steps:
presetting the service life of the cooling tank as N;
calculating the thinning limit times of the thrust chamber wall material to be NT；
Mixing N with NTCarrying out comparison;
when N is present<NTIf the stretching is unstable and invalid, designing parameters according to a calculation method of the stretching unstable and invalid; when N is present>NTAnd if the fatigue failure is indicated, designing parameters according to a calculation method of the fatigue failure.
Specifically, the method calculates the parameters of the cooling tank according to the given service life, solves the problem that in the prior art, the complicated step of checking whether the service life of the cooling tank is qualified after the parameters of the cooling tank are designed firstly is solved, does not need any simulation calculation process in the calculation process, is simple, convenient and effective, and has strong engineering practical significance.
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In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a flow chart of a reusable rocket engine thrust chamber cooling slot parameter design method provided herein.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Example one
With reference to fig. 1, the present application provides a method for designing parameters of a reusable rocket engine thrust chamber cooling slot, comprising the following steps:
presetting the service life of the cooling tank as N;
calculating the thinning limit times of the thrust chamber wall material to be NT；
Mixing N with NTCarrying out comparison;
when N is present<NTAnd (4) when the stretching is unstable and ineffective, designing parameters according to a calculation method of the stretching unstable and ineffective.
Specifically, in the embodiment, a thrust chamber of a certain high-thrust oxyhydrogen rocket engine is selected as a research object, and the inner wall material of the thrust chamber is OFHC.
Step 100: presetting the service life N of the cooling tank as 100 times; step 200: calculating NTWhen N is 0.467, N isT＝750n1.25＝750×0.4671.25＝289；
Step 300: mixing N with NTComparison is made, at this time N<NTAt this time, the stretching is unstable and fails;
the service life N expression can be obtained according to the geometric relation of the deformation and the failure of the cooling groove as follows:
h is the thickness of the inner wall of the cooling groove, L is the width of a cooling channel of the cooling groove, W is the thickness of a ribbed plate of the cooling groove, and delta is the total deformation of the inner wall of the cooling groove.
Wherein the total deformation delta of the inner wall is determined by the bending deformation delta of the inner wall1And amount of shear deformation δ2Composition, P ═ 5.02 × 106pa:
Namely the following formula:
axial strain delta epsilon in thisp1Of axial inelastic strain Deltaε 'caused by the different coefficients of thermal expansion of the inner and outer walls of the cooling bath'p1And axial strain delta epsilon due to thermal stress "p1The structure specifically comprises the following formula:
when alpha is 1.71X 10-5，v＝0.3，E＝1.17×1011，Sy＝6.2×107pa；
When the current is over;
calculated by the one-dimensional heat transfer of the thrust chamber, k is 352 heat conductivity coefficient, T4Coolant temperature, T, 7613400 is gas temperature, Ma is 1 at throat, available:
when different X values are selected, the corresponding Y values are obtained and can be fitted into a quadratic function relationship, so that T is obtained2、T3The value of (c):
T2＝(-0.6183X2+0.871X+0.1571)T1
the life expression of the cooling tank in the case of unstable stretching failure can be obtained by integrating the steps as follows:
a set of parameters can thus be found from the life expression of the cooling bath at the time of a tensile instability failure, for example: l is 1.8338 mm; w is 1.2 mm; h is 4 mm; h is 0.337 mm; in conclusion, the method realizes the purpose of setting the service life and then calculating the parameters of the cooling tank, and the process does not need any simulation calculation process, thereby being simple, convenient and effective.
Example two
The application provides a reusable rocket engine thrust chamber cooling groove parameter design method, which comprises the following steps:
presetting the service life of the cooling tank as N;
calculating the thinning limit times of the thrust chamber wall material to be NT；
Mixing N with NTCarrying out comparison;
when N is present>NTAnd if the fatigue failure is indicated, designing parameters according to a calculation method of the fatigue failure.
Step 100: presetting the service life N of the cooling tank to be 800 times; step 200: calculating NTWhen N is 0.467, N isT＝750n1.25＝750×0.4671.25＝289；
Step 300: mixing N with NTComparison is made, at this time N>NTI.e., the fatigue failure at this time;
according to the Manson-coffee fatigue life formula, the method comprises the following steps:
from the plastic deformation formula, the minimum cross section effectively becomes:
wherein epsilon1minAnd ε2minRespectively representing the radial minimum section strain and the axial minimum section strain, epsilon1minAnd ε2minAs follows:
wherein,
from the geometrical relationship it can be found that:
wherein, δ, T2、T3The values of (a) are the same as the calculation procedure and results in embodiment one.
The fatigue life parameter expression can be obtained by integrating the steps:
a set of parameters can therefore be found from the fatigue life parameter expression, for example:
L＝1.5338mm；W＝1.5mm；h＝6mm；H＝0.0.625mm。
in conclusion, the method realizes the purpose of setting the service life and then calculating the parameters of the cooling tank, and the process does not need any simulation calculation process, thereby being simple, convenient and effective.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application. Moreover, those skilled in the art will appreciate that while some embodiments herein include some features included in other embodiments, rather than other features, combinations of features of different embodiments are meant to be within the scope of the application and form different embodiments.
Claims (10)
1. A reusable rocket engine thrust chamber cooling groove parameter design method is characterized by comprising the following steps:
presetting the service life of the cooling tank as N;
calculating the thinning limit times of the thrust chamber wall material to be NT；
Mixing N with NTCarrying out comparison;
when N is present<NTIf the stretching is unstable and invalid, designing parameters according to a calculation method of the stretching unstable and invalid; when N is present>NTAnd if the fatigue failure is indicated, designing parameters according to a calculation method of the fatigue failure.
2. The method of designing parameters for a reusable rocket engine thrust chamber cooling slot of claim 1 wherein said limiting number of thinning of the thrust chamber inner wall is calculated as NTThe following calculation is carried out by the formula (1):
NT＝750n1.25 (1)
wherein,
wherein s isuIs a material poleA limit strength (Pa); syThe material yield strength (Pa).
3. A method of designing reusable rocket engine thrust chamber cooling slot parameters according to claim 2 wherein said when N is<NTIf the tensile instability failure is indicated, the parameter design according to the calculation method of the tensile instability failure comprises the following steps:
obtaining the temperatures of the gas side inner wall and the coolant side inner wall of the cooling tank as T2、T3；
According to T2And T3Determining the axial inelastic strain delta epsilon 'caused by the different coefficients of thermal expansion of the inner and outer walls of the cooling slot'p1And axial strain Delta epsilon caused by thermal stress of the cooling groove "p1And is according to Δ ε'p1And. DELTA. epsilon "p1Determination of the axial strain Deltaepsilon of the cooling channelp1；
According to the axial strain Delta epsilon of the cooling groovep1Determining the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2And according to the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2Determining the total deformation delta of the inner wall of the cooling tank;
and determining a functional relation which is satisfied between the service life N of the cooling tank and the parameters H, L and W when the stretching instability fails according to the total deformation delta of the inner wall of the cooling tank.
4. The method of designing parameters for a thrust chamber cooling slot of a re-usable rocket engine as recited in claim 1, wherein said step of calculating the temperature of said cooling slot on the gas side inner wall and the temperature of said cooling slot on the coolant side inner wall are each T2、T3The method comprises the following steps:
t can be obtained by a one-dimensional heat transfer calculation formula of the thrust chamber2The one-dimensional heat transfer calculation of the thrust chamber is shown as formula (2):
wherein,
wherein,
calculating T according to the formula (3)3：
Wherein,
wherein k is the thermal conductivity, T4Is the coolant temperature, T1Is the gas temperature, h is the cooling channel height, Ma is the Mach number, mu is the gas viscosity, DtIs the throat diameter, prIs the prandtl number of the coolant, cpFor gas mean mass constant pressure heat capacity, pcIs the combustion chamber pressure, c*For characteristic velocity, R is the throat radius of curvature, AtIs the throat area, A is the axial cross-sectional area, gamma is the specific heat ratio of the fuel gas, h1Is the convective heat transfer coefficient; re is Reynolds number, prwIs the Prandtl number, lambda, of the coolant at the wallfIs the heat conductivity of the coolant, deIs the hydraulic diameter.
5. A method of designing reusable rocket engine thrust chamber cooling slot parameters according to claim 4 wherein the axial strain of the cooling slot Δ εp1According to the formula (4)) Calculating to obtain:
wherein alpha is the coefficient of thermal expansion of the inner wall, v is the Poisson's ratio, E is the elastic modulus of the inner wall,
is constant and equal to 0.35.
6. A method of designing reusable rocket engine thrust chamber cooling slot parameters according to claim 5 wherein said step of determining axial strain Δ ε of said cooling slotp1Determining the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2And according to the bending deformation delta of the inner wall of the cooling groove1And amount of shear deformation δ2Determining the total deformation delta of the inner wall of the cooling tank, and calculating according to a formula (5):
h is the thickness of the inner wall of the cooling groove, L is the width of a cooling channel of the cooling groove, and W is the thickness of a ribbed plate of the cooling groove.
7. The method of designing parameters for a thrust chamber cooling slot of a re-usable rocket engine as recited in claim 6, wherein said step of determining the functional relationship satisfied between the life N of said cooling slot and the parameters H, L and W when said tensile instability failure is determined based on the total deformation δ of the inner wall of said cooling slot comprises the steps of:
the expression for determining the service life N of the cooling tank according to the deformation failure of the cooling tank is shown in the formula (6):
wherein e is a constant;
substituting the formula (5) into the formula (6) to obtain the formula (7):
8. a method of designing reusable rocket engine thrust chamber cooling slot parameters according to claim 7 wherein said equation N is>NTIf the fatigue failure is indicated, the parameter design according to the fatigue failure calculation method comprises the following steps:
the relation for determining the fatigue life parameter is shown as the formula (8):
wherein,
represents the minimum cross-sectional effective strain, NFB and c are constants related to material characteristics, namely the fatigue life of the thrust chamber;
from the plastic deformation formula, the minimum cross section has an effect as shown in formula (9):
wherein epsilon1minAnd ε2minRespectively representing the radial minimum section strain and the axial minimum section strain, epsilon1minAs shown in equation (10), ε2minAs shown in formula (11):
wherein epsilon1avg＝ε2min，
Order to
Namely, the relation of fatigue life parameters is obtained as shown in the formula (12):
9. the method of designing reusable rocket engine thrust chamber cooling slot parameters of claim 8,
substituting the parameter obtained by the formula (12) into the formula (7) obtains a result larger than NT。
10. The method of claim 8, wherein when the thrust chamber wall material is Narloy-Z, b is 0.549, c is-0.4844; when the material of the inner wall of the thrust chamber is the OFHC function, b is 0.1669, and c is-0.44.
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| CN114139309A (en) * | 2021-11-24 | 2022-03-04 | 中国人民解放军国防科技大学 | Method for estimating service life of thrust chamber of liquid rocket engine |
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