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

Abstract

The invention discloses a method for evaluating a flow path in a turbopump of a liquid rocket engine, and relates to the technical field of design of turbopumps of rocket engines. The method comprises the following steps: determining an axial force score value of the turbopump based on the axial force of the turbopump; based on the centrifugal wheel rear cavity pressure of the oxidant pump and the fuel pump, a centrifugal wheel rear cavity pressure score value of the turbine pump is determined; based on the end face seal pressure of the oxidant pump and the fuel pump, the end face seal pressure score value of the turbine pump is determined; determining a flow velocity score value in the return pipe of the turbine pump based on the flow velocity in the return pipe of the oxidant pump and the fuel pump; based on the axial force score value of the turbine pump, the centrifugal wheel rear cavity pressure score value, the end face sealing position pressure score value and the backflow pipe inner flow speed score value, the inner flow path evaluation total score of the turbine pump is determined, and therefore accurate quantitative evaluation can be conducted on the liquid rocket engine turbine pump inner flow path based on the inner flow path evaluation total score of the turbine pump.

Description

Technical Field

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

[0002] The liquid rocket engine turbopump consists of three major components: an oxidizer pump, a fuel pump, and a 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. For liquid rocket engines, the design and accurate calculation of the internal flow paths of the oxidizer pump and the 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 clear and standardized evaluation methods for the internal flow paths of turbopumps, which brings risks to the research and development and design of liquid rocket engine turbopumps.

[0003] Aiming at the above problems, a method for evaluating the internal flow path of a liquid rocket engine turbopump was developed. Summary of the invention

[0004] An embodiment of the present invention provides a method for evaluating the internal flow path of a liquid rocket engine turbopump, aiming to solve the problem that the prior art cannot accurately evaluate the internal flow path of a liquid rocket engine turbopump.

[0005] An embodiment of the present invention provides a method for evaluating the flow path in a liquid rocket engine turbopump, wherein the turbopump includes an oxidizer pump, a fuel pump, and a turbine. The method includes:

[0006] Acquiring an axial force of a turbopump, and determining an axial force score of the turbopump based on the axial force of the turbopump;

[0007] Acquire the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump, and determine the centrifugal wheel rear chamber pressure score value of the turbo pump based on the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump;

[0008] Obtaining the pressure at the end face seal of the oxidant pump and the fuel pump, and determining the pressure score value at the end face seal of the turbo pump based on the pressure at the end face seal of the oxidant pump and the fuel pump;

[0009] Acquire the flow velocities in the return pipes of the oxidant pump and the fuel pump, and determine a flow velocity score value in the return pipe of the turbo pump based on the flow velocities in the return pipes of the oxidant pump and the fuel pump;

[0010] The total score of the internal flow path evaluation of the turbine pump is determined based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe.

[0011] A further technical solution is that obtaining the axial force of the turbine pump comprises:

[0012] Based on the structural parameters of the turbopump, determining the axial force calculation perimeter of the turbopump;

[0013] Determining the axial forces of the oxidizer pump, the fuel pump and the turbine of the turbopump respectively based on the axial force calculation perimeter;

[0014] The axial force of the turbopump is determined based on the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbopump.

[0015] A further technical solution is that the axial forces of the oxidizer pump, the fuel pump and the turbine of the turbo pump are determined based on the axial force calculation perimeter, including:

[0016] By formula Calculate the axial forces of the oxidant pump, fuel pump and turbine of the turbo pump, where R z is the axial force, p is the static pressure of the peripheral fluid, F z is the projection of the peripheral interface on the plane perpendicular to the z-axis, q m is the mass flow rate of the fluid passing through the impeller, c 1z is the axial velocity of the fluid at the impeller inlet, c 1z is the axial velocity of the fluid at the impeller outlet.

[0017] A further technical solution is that the axial force of the turbopump is determined based on the axial forces of the oxidant pump, the fuel pump and the turbine of the turbopump, including:

[0018] The sum of the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbo pump is calculated as the axial force of the turbo pump.

[0019] A further technical solution is that the axial force score of the turbopump is determined based on the axial force of the turbopump, including:

[0020] Determining whether the axial force of the turbo pump satisfies a preset direction and is less than a preset axial force threshold;

[0021] If the axial force of the turbo pump satisfies a preset direction and is less than a preset axial force threshold, determining that the axial force score of the turbo pump is a preset first score;

[0022] If the axial force of the turbo pump does not satisfy a preset direction or is not less than a preset axial force threshold, it is determined that the axial force score of the turbo pump is a preset second score.

[0023] A further technical solution is that the centrifugal wheel rear cavity pressure score value of the turbo pump is determined based on the centrifugal wheel rear cavity pressures of the oxidant pump and the fuel pump, including:

[0024] Determining whether the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold;

[0025] If the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset third score value;

[0026] If the pressure of the centrifugal wheel rear chamber of the oxidant pump is not less than a preset first centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset fourth score value;

[0027] Determining whether the pressure of the centrifugal wheel rear chamber of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold;

[0028] If the centrifugal wheel rear chamber pressure of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset fifth score value;

[0029] If the centrifugal wheel rear chamber pressure of the fuel pump is not less than a preset second centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset sixth score value;

[0030] The sum of the score value of the centrifugal wheel rear chamber pressure of the oxidant pump and the score value of the centrifugal wheel rear chamber pressure of the fuel pump is calculated as the score value of the centrifugal wheel rear chamber pressure of the turbo pump.

[0031] A further technical solution is that the pressure score value at the end face seal of the turbo pump is determined based on the pressure at the end face seal of the oxidant pump and the fuel pump, including:

[0032] Determining whether the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold;

[0033] If the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold, the score value of the pressure at the end face seal of the oxidant pump is determined to be a preset seventh score value;

[0034] If the pressure at the end face seal of the oxidant pump is not less than a preset first end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the oxidant pump is a preset eighth score value;

[0035] Determining whether the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold;

[0036] If the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the fuel pump is a preset ninth score value;

[0037] If the pressure at the end face seal of the fuel pump is not less than a preset second end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the fuel pump is a preset tenth value;

[0038] The sum of the score value of the pressure at the end face seal of the oxidizer pump and the score value of the pressure at the end face seal of the fuel pump is calculated as the score value of the pressure at the end face seal of the turbo pump.

[0039] A further technical solution is that obtaining the flow rate in the return pipe of the oxidant pump and the fuel pump includes:

[0040] By formula V 氧回流 =q V氧回流 / S m氧回流 Calculate the flow rate in the reflux pipe of the oxidant pump, where V 氧回流 is the flow rate in the reflux pipe of the oxidant pump, q V氧回流 is the oxygen reflux volume flow rate of the oxidant pump, S V氧回流 is the cross-sectional area of ​​the oxygen reflux pipe of the oxidant pump;

[0041] By formula V 燃料回流 =q V燃料回流 / S m燃料回流 Calculate the flow rate in the return pipe of the fuel pump, where V 燃料回流 is the flow velocity in the return pipe of the fuel pump, q V燃料回流 is the fuel return volume flow rate of the fuel pump, S V燃料回流 is the cross-sectional area of ​​the fuel return pipe of the fuel pump.

[0042] A further technical solution is that the flow rate score value in the return pipe of the turbo pump is determined based on the flow rates in the return pipes of the oxidant pump and the fuel pump, including:

[0043] Determining whether the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold;

[0044] If the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold, determining that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset eleventh score value;

[0045] If the flow rate in the reflux pipe of the oxidant pump is not less than a preset first reflux pipe flow rate threshold, determining that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset twelfth score value;

[0046] Determining whether the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold;

[0047] If the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold, determining that the score value of the flow velocity in the return pipe of the fuel pump is a preset thirteenth value;

[0048] If the flow velocity in the return pipe of the fuel pump is not less than a preset second return pipe flow velocity threshold, determining that the score value of the flow velocity in the return pipe of the fuel pump is a preset fourteenth score value;

[0049] The sum of the score value of the flow rate in the return pipe of the oxidant pump and the score value of the flow rate in the return pipe of the fuel pump is calculated as the score value of the flow rate in the return pipe of the turbo pump.

[0050] A further technical solution is that the total score of the internal flow path evaluation of the turbine pump is determined based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe, including:

[0051] The sum of the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe is calculated as the total score of the internal flow path evaluation of the turbine pump.

[0052] An embodiment of the present invention provides a method for evaluating the flow path in a liquid rocket engine turbine pump. The method includes: obtaining the axial force of the turbine pump, and determining the axial force score of the turbine pump based on the axial force of the turbine pump; obtaining the pressure of the centrifugal wheel rear chamber of the oxidizer pump and the fuel pump, and determining the pressure score of the centrifugal wheel rear chamber of the turbine pump based on the pressure of the centrifugal wheel rear chamber of the oxidizer pump and the fuel pump; obtaining the pressure at the end face seal of the oxidizer pump and the fuel pump, and determining the pressure score of the end face seal of the turbine pump based on the pressure of the end face seal of the oxidizer pump and the fuel pump; obtaining the pressure .... and the flow rate in the return pipe of the fuel pump, based on the flow rates in the return pipes of the oxidizer pump and the fuel pump, determine the flow rate score in the return pipe of the turbine pump; based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal and the flow rate score in the return pipe, determine the total score for the internal flow path evaluation of the turbine pump, so as to accurately and quantitatively evaluate the internal flow path of the liquid rocket engine turbine pump based on the total score for the internal flow path evaluation of the turbine pump, and provide a reliable reference for the research, development and design of liquid rocket engine turbine pumps. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] 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.

[0054] Figure 1 A schematic flow chart of a method for evaluating the flow path in a liquid rocket engine turbopump provided by an embodiment of the present invention;

[0055] Figure 2 In a method for evaluating the internal flow path of a liquid rocket engine turbine pump provided in an embodiment of the present invention, a schematic diagram for determining the axial force acting on an impeller is provided. In the figure, (a) is a centrifugal pump with an inducer; and (b) is an axial flow turbine. DETAILED DESCRIPTION

[0056] 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.

[0057] 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.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] See also Figure 1 The present invention provides a schematic flow chart of a method for evaluating the flow path in a liquid rocket engine turbo pump. The turbo pump includes an oxidizer pump, a fuel pump, and a turbine. Figure 1 As shown, the method comprises the following steps: S1-S5

[0062] S1, obtaining the axial force of the turbopump, and determining the axial force score value of the turbopump based on the axial force of the turbopump.

[0063] In a specific implementation, the present invention calculates and obtains the axial force of the turbopump, wherein the axial force of the turbopump includes the direction and magnitude of the force. Then, based on the axial force of the turbopump and the set evaluation criteria, the axial force score of the turbopump is determined.

[0064] Specifically, in one embodiment, the above step of “obtaining the axial force of the turbine pump” includes the following steps:

[0065] S11, determining an axial force calculation perimeter of the turbopump based on structural parameters of the turbopump.

[0066] In a specific implementation, in the present invention, the axial force calculation perimeter of the turbopump is determined based on the structural parameters of the turbopump. The axial force calculation perimeter of the turbopump includes the axial force calculation perimeters of the oxidant pump, the fuel pump and the turbine.

[0067] For example, see Figure 2 ,exist Figure 2 For the turbo pumps shown, for the oxidizer pump and the fuel pump, see Figure 2 In (a), the calculation boundary of the axial force is determined as For turbines, see Figure 2 In (b), the calculation boundary of the axial force is determined to be aa1δδ1.

[0068] S12, determining the axial forces of the oxidizer pump, the fuel pump and the turbine of the turbopump respectively based on the axial force calculation perimeter;

[0069] In a specific implementation, the axial forces of the oxidant pump, the fuel pump and the turbine of the turbo pump are calculated in the same manner. For example, in this embodiment, the formula Calculate the axial forces of the oxidant pump, fuel pump and turbine of the turbo pump, where R z is the axial force, p is the static pressure of the peripheral fluid, F z is the projection of the peripheral interface on the plane perpendicular to the z-axis, q m is the mass flow rate of the fluid passing through the impeller, c 1z is the axial velocity of the fluid at the impeller inlet, c 1z is the axial velocity of the fluid at the impeller outlet.

[0070] S13, determining the axial force of the turbopump based on the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbopump.

[0071] In a specific implementation, the sum of the axial forces of the oxidant pump, the fuel pump and the turbine of the turbopump is calculated as the axial force of the turbopump. That is, the axial forces of the oxidant pump, the fuel pump and the turbine of the turbopump are added together to obtain the axial force of the turbopump.

[0072] The axial force R of the turbine pump is expressed by the formula: z涡轮泵 =R z氧化剂泵 +R z燃料泵 +R z涡轮 , where R z涡轮泵 is the axial force of the turbine pump, R z氧化剂泵 is the axial force of the oxidant pump, R z燃料泵 is the axial force of the fuel pump, R z涡轮 is the axial force of the turbine.

[0073] In one embodiment, the above step of “determining the axial force score of the turbopump based on the axial force of the turbopump” specifically includes the following steps:

[0074] S101, determining whether the axial force of the turbine pump satisfies a preset direction and is less than a preset axial force threshold.

[0075] In the specific implementation, it is determined whether the axial force of the turbine pump meets the requirements: R z涡轮泵 <R zMax , and R z涡轮泵 If the above conditions are met, the axial force score is determined to be a preset first score (eg, 1), otherwise, the axial force score of the turbine pump is determined to be a second score (eg, 0).

[0076] S102: If the axial force of the turbo pump satisfies a preset direction and is less than a preset axial force threshold, determine that the axial force score of the turbo pump is a preset first score.

[0077] In a specific implementation, if the axial force of the turbo pump is less than a preset axial force threshold, the axial force score of the turbo pump is determined to be a preset first score, and in an embodiment of the present invention, the first score can be set to 1. It can be understood that the first score can be specifically set by a person skilled in the art, and the present invention does not specifically limit it.

[0078] S103: If the axial force of the turbo pump does not satisfy a preset direction or is not less than a preset axial force threshold, determine that the axial force score of the turbo pump is a preset second score.

[0079] In a specific implementation, if the axial force of the turbine pump does not meet the preset direction or is not less than the preset axial force threshold, the axial force score of the turbine pump is determined to be a preset second score. In an embodiment of the present invention, the second score can be set to 0. It can be understood that the second score can be specifically set by a person skilled in the art, and the present invention does not specifically limit it.

[0080] S2, obtaining the centrifugal wheel rear cavity pressures of the oxidant pump and the fuel pump, and determining a centrifugal wheel rear cavity pressure score value of the turbo pump based on the centrifugal wheel rear cavity pressures of the oxidant pump and the fuel pump.

[0081] In a specific implementation, the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump are obtained by measuring or calculating, and then, based on the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump and a preset evaluation standard, the centrifugal wheel rear chamber pressure score of the turbo pump is determined.

[0082] In a specific implementation, the pressure of the centrifugal wheel rear chamber of the oxidant pump and the fuel pump is obtained by experimental measurement or one-dimensional theoretical calculation. For experimental measurement, a pressure measuring point is set in the centrifugal wheel rear chamber, and the pressure is measured and obtained during the generator / turbine pump semi-system test or engine test. For one-dimensional theoretical calculation, the pressure and flow equations of the internal flow path can be established and solved simultaneously to obtain the pressure.

[0083] In one embodiment, the above step of “determining the score value of the centrifugal wheel rear chamber pressure of the turbo pump based on the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump” specifically includes the following steps:

[0084] S21, determining whether the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold.

[0085] In a specific embodiment, it is determined whether the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold. The first centrifugal wheel rear chamber pressure threshold can be set by those skilled in the art and is not specifically limited in the present invention.

[0086] S22: If the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold, determine that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset third score value.

[0087] In a specific embodiment, if the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold, the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is determined to be a preset third score value. In an embodiment of the present invention, the third score value can be set to 0.5. It can be understood that the third score value can be specifically set by those skilled in the art, and the present invention is not specifically limited.

[0088] S23: If the pressure of the centrifugal wheel rear chamber of the oxidant pump is not less than a preset first centrifugal wheel rear chamber pressure threshold, determine that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset fourth score value.

[0089] In a specific embodiment, if the pressure of the centrifugal wheel rear chamber of the oxidant pump is not less than a preset first centrifugal wheel rear chamber pressure threshold, the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is determined to be a preset fourth score value. In an embodiment of the present invention, the fourth score value can be set to 0. It can be understood that the third score value can be specifically set by those skilled in the art, and the present invention is not specifically limited.

[0090] S24, determining whether the pressure of the centrifugal wheel rear chamber of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold.

[0091] In a specific embodiment, it is determined whether the centrifugal wheel rear chamber pressure of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold. The second centrifugal wheel rear chamber pressure threshold can be set by those skilled in the art and is not specifically limited in the present invention.

[0092] S25: If the centrifugal wheel rear chamber pressure of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold, determine that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset fifth score value.

[0093] In a specific embodiment, if the centrifugal wheel rear chamber pressure of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold, the score value of the centrifugal wheel rear chamber pressure of the fuel pump is determined to be a preset fifth score value.

[0094] In the embodiment of the present invention, the fifth score may be set to 0.5. It is understandable that the fifth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0095] S26: If the centrifugal wheel rear chamber pressure of the fuel pump is not less than a preset second centrifugal wheel rear chamber pressure threshold, determine that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset sixth score value.

[0096] In a specific embodiment, if the centrifugal wheel rear chamber pressure of the fuel pump is not less than a preset second centrifugal wheel rear chamber pressure threshold, the score value of the centrifugal wheel rear chamber pressure of the fuel pump is determined to be a preset sixth score value.

[0097] In the embodiment of the present invention, the sixth score may be set to 0. It can be understood that the sixth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0098] S27, calculating the sum of the score value of the centrifugal wheel rear chamber pressure of the oxidant pump and the score value of the centrifugal wheel rear chamber pressure of the fuel pump as the score value of the centrifugal wheel rear chamber pressure of the turbo pump.

[0099] In a specific embodiment, the score value of the centrifugal wheel rear chamber pressure of the oxidant pump and the score value of the centrifugal wheel rear chamber pressure of the fuel pump are added together to obtain the score value of the centrifugal wheel rear chamber pressure of the turbine pump.

[0100] S3, obtaining the pressure at the end face seal of the oxidizer pump and the fuel pump, and determining the pressure score value at the end face seal of the turbo pump based on the pressure at the end face seal of the oxidizer pump and the fuel pump.

[0101] In a specific implementation, the pressure at the end face seal of the oxidant pump and the fuel pump is obtained by measuring or calculating. Then, based on the pressure at the end face seal of the oxidant pump and the fuel pump and a preset evaluation standard, the pressure score value at the end face seal of the turbo pump is determined.

[0102] In a specific implementation, the pressure at the end face seal of the oxidizer pump and the fuel pump is obtained by experimental measurement or one-dimensional theoretical calculation. For experimental measurement, a pressure measuring point is set at the end face seal, and the pressure is measured and obtained during the generator / turbine pump semi-system test or engine test. For one-dimensional theoretical calculation, the pressure and flow equations of the internal flow path can be established and solved simultaneously to obtain the pressure.

[0103] In one embodiment, the above step of "determining the pressure score value at the end face seal of the turbo pump based on the pressure at the end face seals of the oxidizer pump and the fuel pump" specifically includes the following steps:

[0104] S31, determining whether the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold.

[0105] In a specific implementation, it is determined whether the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold. The first end face seal pressure threshold can be set by those skilled in the art and is not specifically limited in the present invention.

[0106] S32: If the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold, determine that the score value of the pressure at the end face seal of the oxidant pump is a preset seventh score value.

[0107] In a specific implementation, if the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold, the score value of the pressure at the end face seal of the oxidant pump is determined to be a preset seventh score value.

[0108] In the embodiment of the present invention, the seventh score may be set to 0.5. It is understandable that the seventh score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0109] S33, if the pressure at the end face seal of the oxidant pump is not less than a preset first end face seal pressure threshold, determine that the score value of the pressure at the end face seal of the oxidant pump is a preset eighth score value.

[0110] In a specific implementation, if the pressure at the end face seal of the oxidant pump is not less than a preset first end face seal pressure threshold, the score value of the pressure at the end face seal of the oxidant pump is determined to be a preset eighth score value.

[0111] In the embodiment of the present invention, the eighth score may be set to 0. It can be understood that the eighth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0112] S34, determining whether the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold.

[0113] In a specific implementation, it is determined whether the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold. The second end face seal pressure threshold can be set by those skilled in the art and is not specifically limited in the present invention.

[0114] S35: If the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold, determine that the score value of the pressure at the end face seal of the fuel pump is a preset ninth score value.

[0115] In a specific implementation, if the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold, the score value of the pressure at the end face seal of the fuel pump is determined to be a preset ninth score value.

[0116] In the embodiment of the present invention, the ninth score may be set to 0.5. It is understandable that the ninth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0117] S36, if the pressure at the end face seal of the fuel pump is not less than a preset second end face seal pressure threshold, determine that the score value of the pressure at the end face seal of the fuel pump is a preset tenth value.

[0118] In a specific implementation, if the pressure at the end face seal of the fuel pump is not less than a preset second end face seal pressure threshold, the score value of the pressure at the end face seal of the fuel pump is determined to be a preset tenth value.

[0119] In the embodiment of the present invention, the tenth value may be set to 0. It can be understood that the tenth value may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0120] S37, calculating the sum of the score value of the pressure at the end face seal of the oxidizer pump and the score value of the pressure at the end face seal of the fuel pump as the score value of the pressure at the end face seal of the turbo pump.

[0121] In a specific implementation, the pressure score value at the end face seal of the oxidant pump and the pressure score value at the end face seal of the fuel pump are added together to obtain the pressure score value at the end face seal of the turbine pump.

[0122] S4, obtaining the flow velocities in the return pipes of the oxidizer pump and the fuel pump, and determining a flow velocity score value in the return pipe of the turbo pump based on the flow velocities in the return pipes of the oxidizer pump and the fuel pump.

[0123] In a specific implementation, the flow rates in the return pipes of the oxidant pump and the fuel pump are obtained by measuring or calculating, and then, based on the flow rates in the return pipes of the oxidant pump and the fuel pump and a preset evaluation standard, a flow rate score value in the return pipe of the turbo pump is determined.

[0124] For example, in one embodiment, the above step of "obtaining the flow rate in the return pipe of the oxidant pump and the fuel pump" specifically includes: using the formula V 氧回流 =q V氧回流 / S m氧回流 Calculate the flow rate in the reflux pipe of the oxidant pump, where V 氧回流 is the flow rate in the reflux pipe of the oxidant pump, q V氧回流 is the oxygen reflux volume flow rate of the oxidant pump, S V氧回流 is the cross-sectional area of ​​the oxygen reflux pipe of the oxidant pump;

[0125] Accordingly, by formula V 燃料回流 =q V燃料回流 / S m燃料回流 Calculate the flow rate in the return pipe of the fuel pump, where V 燃料回流 is the flow velocity in the return pipe of the fuel pump, q V燃料回流 is the fuel return volume flow rate of the fuel pump, S V燃料回流 is the cross-sectional area of ​​the fuel return pipe of the fuel pump.

[0126] In one embodiment, the above step of “determining the flow rate score value in the return pipe of the turbo pump based on the flow rates in the return pipes of the oxidant pump and the fuel pump” specifically includes:

[0127] S41, determining whether the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold.

[0128] In a specific implementation, it is determined whether the flow rate in the reflux pipe of the oxidant pump is less than a preset first flow rate threshold in the reflux pipe. The first flow rate threshold in the reflux pipe can be set by a person skilled in the art, and the present invention does not specifically limit it.

[0129] S42: If the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold, determine that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset eleventh score value.

[0130] In a specific implementation, if the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold, the score value of the flow rate in the reflux pipe of the oxidant pump is determined to be a preset eleventh score value.

[0131] In the embodiment of the present invention, the eleventh score may be set to 0.5. It is understandable that the eleventh score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0132] S43, if the flow rate in the reflux pipe of the oxidant pump is not less than a preset first reflux pipe flow rate threshold, determine that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset twelfth score value.

[0133] In a specific implementation, if the flow rate in the reflux pipe of the oxidant pump is not less than a preset first reflux pipe flow rate threshold, the score value of the flow rate in the reflux pipe of the oxidant pump is determined to be a preset twelfth score value.

[0134] In the embodiment of the present invention, the twelfth score may be set to 0. It can be understood that the twelfth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0135] S44, determining whether the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold.

[0136] In a specific implementation, it is determined whether the flow rate in the return pipe of the fuel pump is less than a preset second return pipe flow rate threshold. The second return pipe flow rate threshold can be set by those skilled in the art and is not specifically limited in the present invention.

[0137] S45: If the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold, determine that the score value of the flow velocity in the return pipe of the fuel pump is a preset thirteenth value.

[0138] In a specific implementation, if the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold, the score value of the flow velocity in the return pipe of the fuel pump is determined to be a preset thirteenth value.

[0139] In the embodiment of the present invention, the tenth value may be set to 0.5. It is understandable that the thirteenth value may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0140] S46: If the flow velocity in the return pipe of the fuel pump is not less than a preset second return pipe flow velocity threshold, determine that the score value of the flow velocity in the return pipe of the fuel pump is a preset fourteenth score value.

[0141] In a specific implementation, if the flow velocity in the return pipe of the fuel pump is not less than a preset second return pipe flow velocity threshold, the score value of the flow velocity in the return pipe of the fuel pump is determined to be a preset fourteenth score value.

[0142] In the embodiment of the present invention, the tenth score may be set to 0. It can be understood that the fourteenth score may be specifically set by those skilled in the art, and the present invention does not specifically limit it.

[0143] S47, calculating the sum of the score value of the flow velocity in the return pipe of the oxidant pump and the score value of the flow velocity in the return pipe of the fuel pump as the score value of the flow velocity in the return pipe of the turbo pump.

[0144] In a specific implementation, the score value of the flow velocity in the return pipe of the oxidant pump and the score value of the flow velocity in the return pipe of the fuel pump are added together to obtain the score value of the flow velocity in the return pipe of the turbine pump.

[0145] S5, determining a total score for the internal flow path evaluation of the turbine pump based on the axial force score of the turbine pump, the centrifugal wheel rear chamber pressure score, the end face seal pressure score, and the return pipe flow velocity score.

[0146] In a specific implementation, the sum of the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe is calculated as the total score of the internal flow path evaluation of the turbine pump.

[0147] For example, in a specific embodiment, the preset scores of the above items are used to comprehensively evaluate the flow path in the turbine pump. As shown in Table 1, the full score of the turbine pump axial force sub-item is 1, the full score of the oxidizer pump and fuel pump centrifugal wheel rear cavity pressure sub-items is 0.5, the full score of the oxidizer pump and fuel pump end face seal pressure sub-items is 0.5, and the full score of the oxidizer pump and fuel pump return pipe velocity sub-items is 0.5. If the sub-items meet the requirements, the full score of the sub-items is obtained; otherwise, 0 points are obtained. Finally, the total score of the evaluation of the flow path in the turbine pump is calculated.

[0148] Table 1 Evaluation table of flow path in turbo pump

[0149]

[0150] The technical solution of the embodiment of the present invention obtains the axial force of the turbine pump, and determines the axial force score of the turbine pump based on the axial force of the turbine pump; obtains the centrifugal wheel rear chamber pressure of the oxidizer pump and the fuel pump, and determines the centrifugal wheel rear chamber pressure score of the turbine pump based on the centrifugal wheel rear chamber pressure of the oxidizer pump and the fuel pump; obtains the pressure at the end face seal of the oxidizer pump and the fuel pump, and determines the pressure score at the end face seal of the turbine pump based on the pressure at the end face seal of the oxidizer pump and the fuel pump; obtains the oxidizer pump and the flow rate in the return pipe of the fuel pump. Based on the flow rates in the return pipes of the oxidizer pump and the fuel pump, the flow rate score in the return pipe of the turbine pump is determined; based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal and the flow rate score in the return pipe, the total score for the internal flow path evaluation of the turbine pump is determined, so that the internal flow path of the liquid rocket engine turbine pump can be accurately and quantitatively evaluated based on the total score for the internal flow path evaluation of the turbine pump, providing a reliable reference for the research, development and design of liquid rocket engine turbine pumps.

[0151] 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.

[0152] 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.

[0153] 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 evaluating the flow path in a liquid rocket engine turbopump, characterized in that: The turbo pump includes an oxidant pump, a fuel pump and a turbine, and the method includes: Acquiring an axial force of a turbopump, and determining an axial force score of the turbopump based on the axial force of the turbopump; Acquire the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump, and determine the centrifugal wheel rear chamber pressure score value of the turbo pump based on the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump; Obtaining the pressure at the end face seal of the oxidant pump and the fuel pump, and determining the pressure score value at the end face seal of the turbo pump based on the pressure at the end face seal of the oxidant pump and the fuel pump; Acquire the flow velocities in the return pipes of the oxidant pump and the fuel pump, and determine a flow velocity score value in the return pipe of the turbo pump based on the flow velocities in the return pipes of the oxidant pump and the fuel pump; The total score of the internal flow path evaluation of the turbine pump is determined based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe.

2. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of obtaining the axial force of the turbine pump comprises: Based on the structural parameters of the turbopump, determining the axial force calculation perimeter of the turbopump; Determining the axial forces of the oxidizer pump, the fuel pump and the turbine of the turbopump respectively based on the axial force calculation perimeter; The axial force of the turbopump is determined based on the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbopump.

3. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 2, characterized in that: The step of respectively determining the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbopump based on the axial force calculation perimeter includes: By formula Calculate the axial forces of the oxidant pump, fuel pump and turbine of the turbo pump, where R z is the axial force, p is the static pressure of the peripheral fluid, F z is the projection of the peripheral interface on the plane perpendicular to the z-axis, q m is the mass flow rate of the fluid passing through the impeller, c 1z is the axial velocity of the fluid at the impeller inlet, c 1z is the axial velocity of the fluid at the impeller outlet.

4. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 3, characterized in that: The step of determining the axial force of the turbopump based on the axial forces of the oxidant pump, the fuel pump, and the turbine of the turbopump comprises: The sum of the axial forces of the oxidizer pump, the fuel pump, and the turbine of the turbo pump is calculated as the axial force of the turbo pump.

5. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of determining the axial force score of the turbopump based on the axial force of the turbopump comprises: Determining whether the axial force of the turbo pump satisfies a preset direction and is less than a preset axial force threshold; If the axial force of the turbo pump satisfies a preset direction and is less than a preset axial force threshold, determining that the axial force score of the turbo pump is a preset first score; If the axial force of the turbo pump does not satisfy a preset direction or is not less than a preset axial force threshold, it is determined that the axial force score of the turbo pump is a preset second score.

6. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of determining the centrifugal wheel rear chamber pressure score value of the turbo pump based on the centrifugal wheel rear chamber pressures of the oxidant pump and the fuel pump comprises: Determining whether the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold; If the pressure of the centrifugal wheel rear chamber of the oxidant pump is less than a preset first centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset third score value; If the pressure of the centrifugal wheel rear chamber of the oxidant pump is not less than a preset first centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the oxidant pump is a preset fourth score value; Determining whether the pressure of the centrifugal wheel rear chamber of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold; If the centrifugal wheel rear chamber pressure of the fuel pump is less than a preset second centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset fifth score value; If the centrifugal wheel rear chamber pressure of the fuel pump is not less than a preset second centrifugal wheel rear chamber pressure threshold, determining that the score value of the centrifugal wheel rear chamber pressure of the fuel pump is a preset sixth score value; The sum of the score value of the centrifugal wheel rear chamber pressure of the oxidant pump and the score value of the centrifugal wheel rear chamber pressure of the fuel pump is calculated as the score value of the centrifugal wheel rear chamber pressure of the turbo pump.

7. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of determining the pressure score value at the end face seal of the turbo pump based on the pressure at the end face seals of the oxidizer pump and the fuel pump comprises: Determining whether the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold; If the pressure at the end face seal of the oxidant pump is less than a preset first end face seal pressure threshold, the score value of the pressure at the end face seal of the oxidant pump is determined to be a preset seventh score value; If the pressure at the end face seal of the oxidant pump is not less than a preset first end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the oxidant pump is a preset eighth score value; Determining whether the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold; If the pressure at the end face seal of the fuel pump is less than a preset second end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the fuel pump is a preset ninth score value; If the pressure at the end face seal of the fuel pump is not less than a preset second end face seal pressure threshold, determining that the score value of the pressure at the end face seal of the fuel pump is a preset tenth value; The sum of the score value of the pressure at the end face seal of the oxidizer pump and the score value of the pressure at the end face seal of the fuel pump is calculated as the score value of the pressure at the end face seal of the turbo pump.

8. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The obtaining of the flow rates in the return pipes of the oxidant pump and the fuel pump comprises: By formula V 氧回流 =q V氧回流 / S m氧回流 Calculate the flow rate in the reflux pipe of the oxidant pump, where V 氧回流 is the flow rate in the reflux pipe of the oxidant pump, q V氧回流 is the oxygen reflux volume flow rate of the oxidant pump, S V氧回流 is the cross-sectional area of ​​the oxygen reflux pipe of the oxidant pump; By formula V 燃料回流 =q V燃料回流 / S m燃料回流 Calculate the flow rate in the return pipe of the fuel pump, where V 燃料回流 is the flow velocity in the return pipe of the fuel pump, q V燃料回流 is the fuel return volume flow rate of the fuel pump, S V燃料回流 is the cross-sectional area of ​​the fuel return pipe of the fuel pump.

9. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of determining a flow rate score value in the return pipe of the turbo pump based on the flow rates in the return pipes of the oxidant pump and the fuel pump comprises: Determining whether the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold; If the flow rate in the reflux pipe of the oxidant pump is less than a preset first reflux pipe flow rate threshold, determining that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset eleventh score value; If the flow rate in the reflux pipe of the oxidant pump is not less than a preset first reflux pipe flow rate threshold, determining that the score value of the flow rate in the reflux pipe of the oxidant pump is a preset twelfth score value; Determining whether the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold; If the flow velocity in the return pipe of the fuel pump is less than a preset second return pipe flow velocity threshold, determining that the score value of the flow velocity in the return pipe of the fuel pump is a preset thirteenth value; If the flow velocity in the return pipe of the fuel pump is not less than a preset second return pipe flow velocity threshold, determining that the score value of the flow velocity in the return pipe of the fuel pump is a preset fourteenth score value; The sum of the score value of the flow rate in the return pipe of the oxidant pump and the score value of the flow rate in the return pipe of the fuel pump is calculated as the score value of the flow rate in the return pipe of the turbo pump.

10. The method for evaluating the flow path in a liquid rocket engine turbopump according to claim 1, characterized in that: The step of determining the total score of the internal flow path evaluation of the turbine pump based on the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe comprises: The sum of the axial force score of the turbine pump, the pressure score of the centrifugal wheel rear chamber, the pressure score at the end face seal, and the flow velocity score in the return pipe is calculated as the total score of the internal flow path evaluation of the turbine pump.

Images