Method for calculating internal flow path of turbine pump of liquid rocket engine

Abstract

The invention discloses a liquid rocket engine turbine pump internal flow path calculation method, which relates to the technical field of rocket engines, and comprises the following steps: determining inducer outlet pressure P6 and centrifugal wheel outlet pressure P2 of a propellant pump by using input parameters of the propellant pump; drawing an internal flow path node logic diagram of the propellant pump; obtaining pressure distribution PD in a gap between a centrifugal wheel of the propellant pump and a pump shell; acquiring a flow coefficient and a through-flow area of an inner flow path node of the propellant pump; an inner flow path pressure and flow balance equation set is established, and the pressure of an inner flow path node of the propellant pump and the volume flow of an inner flow path of the propellant pump are determined; a mass flow rate of the inner flow path of the propellant pump and a return line flow rate are determined based on the volume flow rate of the inner flow path of the propellant pump. By means of the technical scheme, the internal flow path parameters of the propellant pump of the liquid rocket engine turbine pump can be obtained through systematic calculation, reference is provided for forward research and development design of the liquid rocket engine turbine pump, and therefore the risk is effectively reduced.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, and in particular to a method for calculating the internal flow path of a turbopump of a liquid rocket engine. Background Art

[0002] The liquid rocket engine turbo pump consists of three major components: the oxidizer pump, the fuel pump, and the turbine. There are internal flow circuits in the oxidizer pump and the fuel pump. After the propellant flows out of the pump centrifugal wheel, most of it enters the volute to reduce speed and increase pressure, and is provided to the engine thrust chamber for combustion to generate thrust. A small part of the propellant flows out through the gap between the centrifugal wheel and the pump casing, flows through and cools the bearings, and finally flows back to the low-pressure area of ​​the pump from the internal flow path of the main shaft or the external return pipe to form an internal flow path.

[0003] For liquid rocket engines, the design and accurate calculation of the flow paths in the oxidizer pump and fuel pump affect the axial force distribution of the turbopump, the pump volumetric efficiency, the bearing cooling effect, etc., and ultimately affect whether the turbopump can operate safely and reliably. At present, there is still a lack of standardized calculation methods for the flow paths in turbopumps, which brings risks to the forward R&D design of liquid rocket engine turbopumps. Summary of the invention

[0004] An embodiment of the present invention provides a method for calculating the internal flow path of a liquid rocket engine turbopump, aiming to solve the problem that there is still a lack of a standardized method for calculating the internal flow path of a turbopump in the prior art, which brings risks to the forward research and development design of liquid rocket engine turbopumps.

[0005] An embodiment of the present invention provides a method for calculating the flow path in a liquid rocket engine turbopump, comprising:

[0006] Using the input parameters of the propellant pump, determine the outlet pressure P of the inducer of the propellant pump 6 And the centrifugal wheel outlet pressure P 2 ;

[0007] According to the internal flow path structure of the propellant pump, a logic diagram of the internal flow path nodes of the propellant pump is drawn;

[0008] Obtain the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ;

[0009] Determine the internal flow path nodes included in the propellant pump according to the internal flow path node logic diagram, and obtain the flow coefficient and flow area of ​​the internal flow path nodes of the propellant pump;

[0010] Establishing an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path node of the propellant pump to determine the pressure of the internal flow path node of the propellant pump and the volume flow of the internal flow path of the propellant pump;

[0011] The mass flow rate of the internal flow path of the propellant pump and the return pipe flow rate are determined based on the volume flow rate of the internal flow path of the propellant pump.

[0012] A further technical solution is that the input parameter is the inlet pressure P of the propellant pump. 1 The induction wheel outlet pressure P of the propellant pump is determined by using the input parameters of the propellant pump. 6 And the centrifugal wheel outlet pressure P 2 ,include:

[0013] A three-dimensional full flow field simulation is performed on the propellant pump, and the inducer outlet pressure P of the propellant pump is determined according to the flow field simulation results. 6 And the centrifugal wheel outlet pressure P 2 , in which the inlet pressure of the propellant pump is set to P during the three-dimensional full flow field simulation. 1 .

[0014] A further technical solution is that the input parameter is the inlet pressure P of the propellant pump. 1 The induction wheel outlet pressure P of the propellant pump is determined by using the input parameters of the propellant pump. 6 And the centrifugal wheel outlet pressure P 2 ,include:

[0015] Through the following formula P 6 =P 1 +ρgh 6 Calculate the inducer outlet pressure P of the propellant pump 6 ;

[0016] Through the following formula P 2 =P 1 +ρgh 2 Calculate the centrifugal impeller outlet pressure P of the propellant pump 2 ;

[0017] Where ρ is the propellant density, g is the gravitational acceleration, h is 6 Propellant pump inducer static pressure head, h 2 The static pressure head from the propellant pump inlet to the centrifugal wheel outlet.

[0018] A further technical solution is that the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is obtained. D ,include:

[0019] The pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is calculated using the pressure assessment model. D .

[0020] A further technical solution is that the pressure evaluation model is an ω / 2 model, and the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is calculated by using the pressure evaluation model. D ,include:

[0021] Through the following formula Calculate the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ; where ρ is the propellant density, u 2 is the impeller speed at the centrifugal wheel outlet of the propellant pump, r D is the radius of the floating ring gap of the propellant pump, r 2 is the radius of the centrifugal impeller outlet of the propellant pump.

[0022] A further technical solution is that the propellant pump is an oxygen pump, and the inner flow path nodes include a floating ring gap node, a bearing node and a return pipe node.

[0023] A further technical solution is that the method of obtaining the flow coefficient and flow area of ​​the internal flow path node of the propellant pump includes:

[0024] Get the flow coefficient μ of the floating ring gap node DA and flow area S DA ;

[0025] Get the flow coefficient μ of the bearing node AC and flow area S AC ;

[0026] Get the flow coefficient μ of the return pipe node C1 and flow area S C1 .

[0027] A further technical solution is to establish an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path node of the propellant pump to determine the pressure of the internal flow path node of the propellant pump and the volume flow of the internal flow path of the propellant pump, including:

[0028] Establish the internal flow path pressure and flow balance equations

[0029] Solve the internal flow path pressure and flow balance equations to determine the pressure P of the bearing node. A , the pressure P of the return pipe node C , the volume flow rate q of the inner flow path of the propellant pump V .

[0030] A further technical solution is to determine the mass flow rate of the inner flow path of the propellant pump based on the volume flow rate of the inner flow path of the propellant pump, including:

[0031] By formula q m =ρq V Calculate the mass flow rate q of the inner flow path of the propellant pump m .

[0032] A further technical solution is to determine the return pipe flow rate of the inner flow path of the propellant pump based on the volume flow of the inner flow path of the propellant pump, including:

[0033] By formula V C1 =q V / S C1 Calculate the return pipe flow rate V of the internal flow path of the propellant pump C1 .

[0034] The embodiment of the present invention provides a method for calculating the flow path of a liquid rocket engine turbo pump, comprising: using the input parameters of the propellant pump to determine the outlet pressure P of the inducer of the propellant pump. 6 And the centrifugal wheel outlet pressure P 2 ; According to the internal flow path structure of the propellant pump, draw the internal flow path node logic diagram of the propellant pump; obtain the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ; Determine the internal flow path nodes included in the propellant pump according to the internal flow path node logic diagram, and obtain the flow coefficient and flow area of ​​the internal flow path nodes of the propellant pump; establish an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path nodes of the propellant pump, and determine the pressure of the internal flow path nodes of the propellant pump and the volume flow of the internal flow path of the propellant pump; determine the mass flow of the internal flow path of the propellant pump and the return pipe flow rate based on the volume flow of the internal flow path of the propellant pump. Through the technical solution of the embodiment of the present invention, the acquired volume flow q of the propellant pump of the liquid rocket engine turbopump can be systematically calculated. V , mass flow rate q m , Reflux pipe velocity V C1 , Inducer outlet pressure P 6 , centrifugal wheel outlet pressure P 2 , Centrifugal wheel rear chamber pressure P A , Bearing rear pressure P C , the pressure P after the gap between the centrifugal wheel and the pump housing D The internal flow path parameters can provide a reference for the forward research and development design of liquid rocket engine turbopumps, thereby effectively reducing risks. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying any creative work.

[0036] Figure 1 A schematic flow chart of a method for calculating the flow path in a liquid rocket engine turbopump provided by an embodiment of the present invention;

[0037] Figure 2 A schematic cross-sectional view of an inner flow path of an oxygen pump provided in an embodiment of the present invention;

[0038] Figure 3 This is a logic diagram of the internal flow path nodes of the oxygen pump provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] It should be understood that when used in this specification and the appended claims, the terms "include" and "comprises" indicate the presence of described features, integers, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or combinations thereof.

[0041] It should also be understood that the terms used in this specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. As used in the specification of the present invention and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include plural forms.

[0042] It should be further understood that the term "and / or" used in the present description and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0043] As used in this specification and the appended claims, the term "if" may be interpreted as "when" or "upon" or "in response to determining" or "in response to detecting," depending on the context. Similarly, the phrases "if it is determined" or "if [described condition or event] is detected" may be interpreted as meaning "upon determination" or "in response to determining" or "upon detection of [described condition or event]" or "in response to detecting [described condition or event]," depending on the context.

[0044] See also Figure 1 , Figure 1 It is a flow chart of a method for calculating the internal flow path of a liquid rocket engine turbine pump provided by an embodiment of the present invention. The liquid rocket engine turbine pump comprises three major components: an oxidizer pump, a fuel pump, and a turbine, wherein the oxidizer pump and the fuel pump belong to the propellant pump, and an internal flow path exists therein. The purpose of the present invention is to calculate the internal flow path of the propellant pump, that is, to calculate the internal flow paths of the oxidizer pump and the fuel pump. In the following embodiments, the oxidizer pump will be taken as an example for explanation. Specifically, the method for calculating the internal flow path of a liquid rocket engine turbine pump comprises the following steps:

[0045] S1, using the input parameters of the propellant pump, determine the outlet pressure P of the inducer of the propellant pump 6 And the centrifugal wheel outlet pressure P 2 .

[0046] In the specific implementation, in this implementation, taking the propellant pump as an oxygen pump as an example, the input parameter is the inlet pressure P of the oxygen pump. 1 According to the input parameters of the propellant pump and the structural characteristics of the propellant pump, the outlet pressure P of the inducer of the propellant pump is determined. 6 And the centrifugal wheel outlet pressure P 2 .

[0047] In one embodiment, the input parameter is the inlet pressure P of the propellant pump. 1 For example, taking the oxygen pump as an example, the input parameter is the inlet pressure P of the oxygen pump. 1 The above step "uses the input parameters of the propellant pump to determine the outlet pressure P of the inducer of the propellant pump 6 And the centrifugal wheel outlet pressure P 2 ”, specifically comprising the following steps: performing a three-dimensional full flow field simulation on the propellant pump, and determining the inducer outlet pressure P of the propellant pump according to the flow field simulation results. 6 And the centrifugal wheel outlet pressure P 2 , wherein, in the three-dimensional full flow field simulation, the inlet pressure of the propellant pump is set to P 1 .

[0048] Specifically, taking the propellant pump as an oxygen pump as an example, a three-dimensional full flow field simulation of the oxygen pump is performed through simulation software, and the inducer outlet pressure P of the oxygen pump is determined according to the flow field simulation results. 6 And the centrifugal wheel outlet pressure P 2 In the three-dimensional full flow field simulation, it is necessary to set the inlet pressure of the oxygen pump. In this embodiment, the inlet pressure of the oxygen pump is set to P 1 .

[0049] In one embodiment, the input parameter is the inlet pressure P of the propellant pump. 1 For example, taking the oxygen pump as an example, the input parameter is the inlet pressure P of the oxygen pump. 1 The above step "uses the input parameters of the propellant pump to determine the outlet pressure P of the inducer of the propellant pump 6 And the centrifugal wheel outlet pressure P 2 ", specifically including the following steps: By the following formula P 6 =P 1 +ρgh 6 Calculate the inducer outlet pressure P of the propellant pump 6 ; Through the following formula P 2 =P 1 +ρgh 2 Calculate the centrifugal impeller outlet pressure P of the propellant pump 2 ; where ρ is the propellant density, g is the gravitational acceleration, h is 6 Propellant pump inducer static pressure head, h 2 The static pressure head from the propellant pump inlet to the centrifugal wheel outlet.

[0050] Taking the propellant pump as an oxygen pump as an example, ρ is the density of liquid oxygen, g is the acceleration due to gravity, h is 6 Oxygen pump inducer static pressure head, h 2 The static pressure head from the oxygen pump inlet to the centrifugal wheel outlet. 1 is 0.35MPa, ρ is 1140kg / m 3 , calculate P 6 1.6MPa, P 2 It is 8.3MPa.

[0051] S2, drawing a logic diagram of the internal flow path nodes of the propellant pump according to the internal flow path structure of the propellant pump.

[0052] For example, if the propellant pump is an oxygen pump, see Figure 2 The internal flow path of the oxygen pump contains 5 nodes, namely the node between the inducer and the centrifugal wheel, the node between the centrifugal wheel and the shell gap, the floating ring gap node, the bearing node, and the return pipe node. The corresponding front and rear state points are 1, 2, D, A, and C respectively.

[0053] Based on the internal flow path structure of the above oxygen pump, draw the internal flow path node logic diagram of the oxygen pump as follows Figure 3 shown. Figure 3 In the internal flow path node logic diagram shown, the oxygen pump inlet pressure is P 1 After being pressurized by the inducer and centrifugal wheel, the pressure at the centrifugal wheel outlet is P 2 , the pressure after passing through the gap between the centrifugal wheel and the pump housing is P D , after passing through the gap of the floating ring, the pressure in the rear chamber of the centrifugal wheel is P A , the pressure after the bearing is P C After passing through the reflux pipe, the pressure at the inlet of the oxygen pump is P 1 The volume flow rate of the oxygen pump is q V Among them, the flow coefficient of the floating ring gap node is μ DA , the flow area is S DA ; The flow coefficient of the bearing node is μ AC , the flow area is S AC ; The flow coefficient of the return pipe node is μ C1 , the flow area is S C1 .

[0054] S3, obtaining the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D .

[0055] In a specific implementation, the pressure evaluation model is used to calculate the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump. D .

[0056] For example, the pressure evaluation model is an ω / 2 model, and the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is calculated using the pressure evaluation model. D ,include:

[0057] Through the following formula Calculate the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ; where ρ is the propellant density, u 2 is the impeller speed at the centrifugal wheel outlet of the propellant pump, r D is the radius of the floating ring gap of the propellant pump, r 2 is the radius of the centrifugal impeller outlet of the propellant pump.

[0058] Taking the propellant pump as an oxygen pump as an example, ρ is the density of liquid oxygen, u 2 is the impeller speed at the centrifugal wheel outlet of the oxygen pump, r D is the radius of the floating ring gap of the oxygen pump, r 2 is the radius of the centrifugal wheel outlet of the oxygen pump. For example, in this embodiment, P DIt is 3.5MPa.

[0059] S4, determining the internal flow path nodes included in the propellant pump according to the internal flow path node logic diagram, and obtaining the flow coefficient and flow area of ​​the internal flow path nodes of the propellant pump.

[0060] In this embodiment, taking the propellant pump as an oxygen pump as an example, the inner flow path nodes include a floating ring gap node, a bearing node, and a return pipe node.

[0061] The above step of "obtaining the flow coefficient and flow area of ​​the inner flow path node of the propellant pump" at least includes: obtaining the flow coefficient μ of the floating ring gap node DA and flow area S DA ; Get the flow coefficient μ of the bearing node AC and flow area S AC ; Get the flow coefficient μ of the return pipe node C1 and flow area S C1 Among them, the flow area is calculated according to the cross-sectional area of ​​the flow structure.

[0062] It can be understood that due to the different flow structures, the flow coefficients of the floating ring gap node, the bearing node and the return pipe node can be calculated according to the following formula:

[0063] μ DA =f 1 (L DA ,δ DA ,λ DA ), where L DA is the floating ring gap length, δ DA is the floating ring gap height, λ DA is the floating ring gap flow resistance coefficient.

[0064] μ AC =f 2 (L C1 ,L C2 ,...,L Cn ), where L Cn It is the nth characteristic dimension of the bearing, where n is a positive integer.

[0065] μ C1 =f 3 (L C1 ,d C1 ,Re C1 ), where L C1 is the return pipe length, d C1 Re is the inner diameter of the return pipe, C1 is the Reynolds coefficient of the working fluid in the reflux pipe.

[0066] Those skilled in the art may also assign values ​​based on experience. The flow coefficients of the floating ring gap node, the bearing node, and the return pipe node are generally in the range of 0.1 to 2.0.

[0067] In this embodiment, the flow coefficient μ of the floating ring gap node is DA is 0.47, the flow coefficient μ of the bearing node AC is 0.83, and the flow coefficient μ of the return pipe node C1 is 0.86, and the flow area S of the floating ring gap node DA 5×10 -5 m 2 , the flow area S of the bearing node AC 2×10 -4 m 2 , the flow area S of the return pipe node C1 7×10 -5 m 2 .

[0068] S5, establishing an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path node of the propellant pump, and determining the pressure of the internal flow path node of the propellant pump and the volume flow of the internal flow path of the propellant pump.

[0069] In the specific implementation, taking the propellant pump as an oxygen pump as an example, the internal flow path pressure flow balance equation group is established

[0070] By solving the above internal flow path pressure and flow balance equations, the pressure P of the bearing node can be obtained. A , the pressure P of the return pipe node C , the volume flow rate q of the inner flow path of the oxygen pump V .

[0071] S6, determining a mass flow rate of the inner flow path of the propellant pump and a return pipe flow rate based on the volume flow rate of the inner flow path of the propellant pump.

[0072] In a specific implementation, the mass flow rate of the inner flow path of the propellant pump and the return pipe flow rate are determined respectively according to the volume flow rate of the inner flow path of the propellant pump.

[0073] Specifically, determining the mass flow rate of the inner flow path of the propellant pump based on the volume flow rate of the inner flow path of the propellant pump includes: using the formula q m =ρq V Calculate the mass flow rate q of the inner flow path of the propellant pump m Among them, taking the propellant pump as an oxygen pump as an example, ρ is the density of liquid oxygen.

[0074] Specifically, determining the return pipe flow rate of the inner flow path of the propellant pump based on the volume flow of the inner flow path of the propellant pump includes: C1 =q V / S C1 Calculate the return pipe flow rate V of the internal flow path of the propellant pump C1 Among them, taking the propellant pump as an oxygen pump as an example, S C1 is the flow area S of the return pipe node of the oxygen pump C1 .

[0075] In this embodiment, the final calculation results in q V 0.0024m 3 / s,q m 2.9kg / s, P D , P A , P C They are 3.6MPa, 1.1MPa and 0.91MPa respectively. C1 It is 35m / s.

[0076] Through the technical solution of the embodiment of the present invention, the volume flow rate q of the propellant pump of the liquid rocket engine turbopump can be obtained by systematic calculation. V , mass flow rate q m , Reflux pipe velocity V C1 , Inducer outlet pressure P 6 , centrifugal wheel outlet pressure P 2 , Centrifugal wheel rear chamber pressure P A , Bearing rear pressure P C , the pressure P after the gap between the centrifugal wheel and the pump housing D The internal flow path parameters can provide a reference for the forward research and development design of liquid rocket engine turbopumps, thereby effectively reducing risks.

[0077] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0078] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

[0079] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present invention, and these modifications or replacements should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A method for calculating the flow path in a liquid rocket engine turbopump, characterized in that: include: Determine the induction wheel outlet pressure P6 and the centrifugal wheel outlet pressure P2 of the propellant pump by using the input parameters of the propellant pump; According to the internal flow path structure of the propellant pump, a logic diagram of the internal flow path nodes of the propellant pump is drawn; Obtain the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ; Determine the internal flow path nodes included in the propellant pump according to the internal flow path node logic diagram, and obtain the flow coefficient and flow area of ​​the internal flow path nodes of the propellant pump; Establishing an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path node of the propellant pump to determine the pressure of the internal flow path node of the propellant pump and the volume flow of the internal flow path of the propellant pump; The mass flow rate of the internal flow path of the propellant pump and the return pipe flow rate are determined based on the volume flow rate of the internal flow path of the propellant pump.

2. The method for calculating the internal flow path of a liquid rocket engine turbopump according to claim 1, characterized in that: The input parameter is the inlet pressure P1 of the propellant pump, and the method of using the input parameter of the propellant pump to determine the induction wheel outlet pressure P6 and the centrifugal wheel outlet pressure P2 of the propellant pump includes: A three-dimensional full flow field simulation is performed on the propellant pump, and the inducer outlet pressure P6 and the centrifugal wheel outlet pressure P2 of the propellant pump are determined according to the flow field simulation results, wherein during the three-dimensional full flow field simulation, the inlet pressure of the propellant pump is set to P1.

3. The method for calculating the internal flow path of a liquid rocket engine turbopump according to claim 1, characterized in that: The input parameter is the inlet pressure P1 of the propellant pump, and the induction wheel outlet pressure P6 and the centrifugal wheel outlet pressure P2 of the propellant pump are determined by using the input parameter of the propellant pump. include: The inducer outlet pressure P6 of the propellant pump is calculated by the following formula P6=P1+ρgh6; The centrifugal wheel outlet pressure P2 of the propellant pump is calculated by the following formula P2=P1+ρgh2; Where, ρ is the propellant density, g is the acceleration due to gravity, h6 is the static pressure head of the propellant pump inducer, and h2 is the static pressure head from the propellant pump inlet to the centrifugal wheel outlet.

4. The method for calculating the internal flow path of a liquid rocket engine turbopump according to claim 1, characterized in that: The pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is obtained. D ,include: The pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is calculated using the pressure assessment model. D .

5. The method for calculating the flow path in a liquid rocket engine turbopump according to claim 4, characterized in that: The pressure evaluation model is an ω / 2 model, and the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump is calculated using the pressure evaluation model. D ,include: Through the following formula Calculate the pressure distribution P in the gap between the centrifugal wheel and the pump housing of the propellant pump D ; where ρ is the propellant density, u2 is the impeller speed at the outlet of the centrifugal wheel of the propellant pump, and r D is the radius of the floating ring gap of the propellant pump, and r2 is the radius of the centrifugal wheel outlet of the propellant pump.

6. The method for calculating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The propellant pump is an oxygen pump, and the inner flow path nodes include a floating ring gap node, a bearing node, and a return pipe node.

7. The method for calculating the flow path in a liquid rocket engine turbopump according to claim 6, characterized in that: The obtaining of the flow coefficient and the flow area of ​​the inner flow path node of the propellant pump comprises: Get the flow coefficient μ of the floating ring gap node DA and flow area S DA ; Get the flow coefficient μ of the bearing node AC and flow area S AC ; Get the flow coefficient μ of the return pipe node C1 and flow area S C1 .

8. The method for calculating the flow path in a liquid rocket engine turbopump according to claim 7, characterized in that: The method of establishing an internal flow path pressure-flow balance equation group based on the flow coefficient and flow area of ​​the internal flow path node of the propellant pump to determine the pressure of the internal flow path node of the propellant pump and the volume flow of the internal flow path of the propellant pump includes: Establish the internal flow path pressure and flow balance equations Solve the internal flow path pressure and flow balance equations to determine the pressure P of the bearing node. A , the pressure P of the return pipe node C , the volume flow rate q of the inner flow path of the propellant pump V .

9. The method for calculating the flow path in a liquid rocket engine turbopump according to claim 8, characterized in that: Determining the mass flow rate of the internal flow path of the propellant pump based on the volume flow rate of the internal flow path of the propellant pump includes: By formula q m =ρq V Calculate the mass flow rate q of the inner flow path of the propellant pump m .

10. The method for calculating the internal flow path of a liquid rocket engine turbopump according to claim 8, characterized in that: Determining a return pipe flow rate of an inner flow path of the propellant pump based on a volume flow of an inner flow path of the propellant pump comprises: By formula V C1 =q V / S C1 Calculate the return pipe flow rate V of the internal flow path of the propellant pump C1 .

Images