CN117094252B - Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system - Google Patents
Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system Download PDFInfo
- Publication number
- CN117094252B CN117094252B CN202311352292.0A CN202311352292A CN117094252B CN 117094252 B CN117094252 B CN 117094252B CN 202311352292 A CN202311352292 A CN 202311352292A CN 117094252 B CN117094252 B CN 117094252B
- Authority
- CN
- China
- Prior art keywords
- labyrinth seal
- seal
- pressure
- calculation
- leakage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 37
- 239000007788 liquid Substances 0.000 title claims abstract description 28
- 238000004364 calculation method Methods 0.000 claims abstract description 79
- 238000007789 sealing Methods 0.000 claims description 25
- 238000013500 data storage Methods 0.000 claims description 17
- 239000012530 fluid Substances 0.000 claims description 10
- 238000005259 measurement Methods 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 7
- 238000012546 transfer Methods 0.000 claims description 7
- 230000009466 transformation Effects 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 11
- 238000004088 simulation Methods 0.000 abstract description 5
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F22/00—Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for
- G01F22/02—Methods or apparatus for measuring volume of fluids or fluent solid material, not otherwise provided for involving measurement of pressure
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Computing Systems (AREA)
- Pure & Applied Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Algebra (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention discloses a method and a system for measuring leakage quantity of a labyrinth seal of a turbopump of a liquid rocket engine, wherein the method comprises the steps of obtaining a first parameter; collecting a second parameter; the second parameter includes a labyrinth seal high pressure inlet side pressure and a labyrinth seal low pressure outlet side pressure; initializing and calculating leakage quantity; performing iterative calculation on the leakage quantity until the calculation error is not larger than the set error; and taking the result of the last iteration as a final calculation result. The invention solves the problems of poor precision, high numerical simulation cost and the like of the traditional empirical formula, and can directly, efficiently and conveniently acquire the real-time labyrinth seal leakage amount in the test.
Description
Technical Field
The invention relates to the technical field of test and test of turbopumps of liquid rocket engines, in particular to a method and a system for measuring leakage of labyrinth seals of a turbopump of a liquid rocket engine.
Background
Turbopumps are the power core of liquid rocket engines. The turbine pump respectively conveys the liquid oxidant and the fuel to the thrust chamber and the gas generator through the high-speed rotation of the centrifugal impeller, and provides necessary energy sources for the launching and the flight of the rocket. Labyrinth seal structures are generally designed around the centrifugal impeller, and the labyrinth seal structures are used for controlling the leakage quantity of the pump within a reasonable range, avoiding potential safety hazards of deflagration of oxidants and fuels caused by overlarge leakage quantity and efficiency reduction caused by volume loss, and simultaneously avoiding faults of shafting instability, leakage and the like caused by insufficient cooling flow of a high-speed bearing and an end face seal assembly caused by overlarge leakage quantity. Therefore, accurate and efficient measurement of the leakage amount of the labyrinth seal of the centrifugal pump is an important subject for further designing and optimizing the turbine pump.
The method for calculating the leakage quantity of the labyrinth seal at home and abroad mainly comprises the following steps: empirical formula, numerical simulation, experimental measurement. The traditional empirical formula takes more dimension parameters of the labyrinth seal into consideration, and takes less state of the labyrinth seal and the fluid, so that the measurement accuracy difference is larger: researchers have proposed a leakage amount calculation model of incompressible ideal fluid through a constant gap, ignoring the turbulent energy transfer effect (assuming a turbulent energy transfer coefficient γ=1), i.e. assuming that fluid energy is transferred in a sealed cavity without damage, and not considering heat energy dissipation; still others have considered the turbulence energy transfer coefficient determined experimentally based on this, but are not well suited for liquid rocket turbopump testing. The numerical calculation is carried out by giving ideal boundary conditions through CFD (Computational Fluid Dynamics), but because the relative size of gaps at the labyrinth seal is small, the grid division is extremely fine, and the required calculation resources, time investment are large and convenience is insufficient. The test measurement is only carried out in a simpler measurement system, and the case of carrying out relevant measurement in the test such as the hot test run is not known at present because of the complexity of the turbine pump structure.
In summary, how to efficiently and accurately measure the leakage amount of the labyrinth seal of the turbopump of the liquid rocket engine is one of the important problems to be solved in the art.
Disclosure of Invention
The invention aims to provide a method and a system for measuring labyrinth seal leakage of a turbopump of a liquid rocket engine, which are used for solving the defects in the prior art, solving the problems of poor precision, high numerical simulation cost and the like of the traditional empirical formula and directly, efficiently and conveniently obtaining the real-time labyrinth seal leakage in the test.
The invention provides a method for measuring leakage of a labyrinth seal of a turbopump of a liquid rocket engine, which comprises the following steps of,
acquiring a first parameter;
collecting a second parameter; the second parameter includes a labyrinth seal high pressure inlet side pressure and a labyrinth seal low pressure outlet side pressure;
initializing and calculating leakage quantity;
performing iterative calculation on the leakage quantity until the calculation error is not larger than the set error;
and taking the iterated leakage amount as a final calculation result.
The liquid rocket engine turbopump labyrinth seal leakage measurement method as described above, wherein optionally the first parameters include radial clearance, seal pitch, seal tooth width, shaft diameter, seal tooth count, fluid density, and hydrodynamic viscosity.
The method for measuring the leakage amount of the labyrinth seal of the turbopump of the liquid rocket engine comprises the following steps of, optionally, each iterative calculation,
calculating the Reynolds number, the turbulent kinetic energy transfer number and the flow coefficient of each sealing cavity according to the initialized calculated leakage amount or the updated leakage amount after the previous iterative calculation;
taking the pressure of the first sealing cavity as the high-pressure inlet side pressure of the labyrinth seal, taking the pressure of the last sealing cavity as the low-pressure outlet side pressure of the labyrinth seal, and calculating the pressure of each sealing cavity;
calculating the leakage quantity and calculation error of the last seal tooth;
updating the leakage amount when the calculation error is not smaller than the set error and the iteration number is not larger than the set number; and when the calculation error is smaller than the set error, exiting the iterative calculation.
The method for measuring the leakage amount of the labyrinth seal of the liquid rocket engine comprises the following steps:
；
wherein,for leakage amount->High pressure inlet side pressure for labyrinth seal, +.>Low pressure outlet side pressure for labyrinth seal, +.>The medium density is the labyrinth seal gap cross-sectional area.
；
Wherein,to seal the axial gap>Is the diameter of the rotating shaft.
The method for measuring the leakage of the labyrinth seal of the liquid rocket engine comprises the following steps:
；
wherein,is Reynolds number (Reynolds number)>For leakage amount->Is the diameter of the rotating shaft>Is powered byViscosity.
The method for measuring the leakage of the labyrinth seal of the liquid rocket engine comprises the following steps of:
wherein,for the turbulent energy transformation coefficient, +.>To seal the axial gap>For sealing the tooth pitch->Is Reynolds number (Reynolds number)>Is the seal tooth width.
The method for measuring the leakage of the labyrinth seal of the liquid rocket engine comprises the following steps:
；
wherein,for the flow coefficient of the first sealed chamber, < >>To seal the axial gap>Is Reynolds number (Reynolds number)>Is the width of the seal teeth;
first, theThe flow coefficient calculation formula of each sealing cavity is as follows:
；
wherein,for the flow coefficient of the first sealed chamber, < >>Is->Flow coefficient of each sealed cavity.
The invention also provides a liquid rocket engine turbopump labyrinth seal leakage measurement system, which comprises,
the first pressure sensor is arranged at the labyrinth seal inlet;
the second pressure sensor is arranged at the labyrinth seal outlet;
the parameter input module is used for acquiring a first parameter;
the data storage module is electrically connected with the first pressure sensor and the second pressure sensor; the data storage module is used for collecting the pressure at the labyrinth seal inlet through the first pressure sensor and collecting the pressure at the labyrinth seal outlet through the second pressure sensor;
the data operation module is electrically connected with the data storage module; the data operation module is used for acquiring the first parameter, the detection result of the first pressure sensor and the detection result of the second pressure sensor through the data storage module to calculate leakage.
According to the liquid rocket engine turbopump labyrinth seal leakage amount measuring and calculating system, the data operation module is used for carrying out iterative calculation according to the labyrinth seal leakage amount calculation formula, the Reynolds number calculation formula, the turbulence energy turning coefficient calculation formula and the flow coefficient calculation formula of each sealing cavity to obtain the final labyrinth seal leakage amount.
The liquid rocket engine turbopump labyrinth seal leakage measuring and calculating system comprises the data display module, wherein the data display module is electrically connected with the data storage module and is used for displaying parameter values in the calculation process and final calculation results.
Compared with the prior art, the method and the device have the advantages that through the pressure of the high-pressure inlet side of the labyrinth seal, the pressure of the low-pressure outlet side of the labyrinth seal and the corresponding first parameters, iterative calculation is carried out according to the relation among the leakage amount of the labyrinth seal, the Reynolds number, the turbulent energy swivel coefficient and the flow coefficient of the sealing cavity, so that the leakage amount of the labyrinth seal of the turbine pump can be calculated. The method overcomes the defects in the prior art, solves the problems of poor precision, high numerical simulation cost and the like of the traditional empirical formula, and can directly, efficiently and conveniently acquire the real-time leakage quantity of the labyrinth seal in the test.
The calculation of the invention considers the flow state in the pump, has higher precision and has about 3 percent of simulation error with CFD; the method can be used for various liquid rocket propellant medium tests, such as: liquid oxygen, kerosene, methane and the like can also be used for measuring and calculating the leakage amount in the hydraulic test, and only medium parameters are required to be modified. The method can be used for calculating the leakage quantity of the labyrinth seal with different tooth numbers, gaps and tooth widths. The labyrinth seal structure with the seal teeth distributed on the stator or the rotor has the same applicability, is convenient and efficient to calculate, and can calculate the leakage in real time.
Drawings
FIG. 1 is a flow chart showing the steps of a method for measuring leakage of a labyrinth seal of a turbopump of a liquid rocket engine according to embodiment 1 of the present invention;
FIG. 2 is a schematic diagram of the mounting structure of a first pressure sensor and a second pressure sensor;
FIG. 3 is a partial cross-sectional view of FIG. 2;
FIG. 4 is an enlarged partial schematic view at A in FIG. 3;
fig. 5 is a block diagram showing the structure of embodiment 2 of the present invention.
Reference numerals illustrate:
1-a first pressure sensor, 2-a second pressure sensor, 3-a labyrinth seal.
Detailed Description
The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
In order to solve the problems set forth in the background art, the present invention proposes the following embodiments.
Example 1
Referring to fig. 1, the embodiment provides a method for measuring leakage of a labyrinth seal of a turbopump of a liquid rocket engine, which includes steps of S1, obtaining a first parameter; specifically, the first parameters include radial clearance, seal pitch, seal tooth width, shaft diameter, seal tooth count, fluid density, and hydrodynamic viscosity. In the implementation, the first parameter has close relation with the engine turbopump, the corresponding labyrinth seal and the corresponding medium, and in the implementation, the first parameter can be preset according to the engine turbopump, the corresponding labyrinth seal and the corresponding medium. In particular, the operator can modify as desired.
S2, collecting a second parameter; the second parameter includes a labyrinth seal high pressure inlet side pressure and a labyrinth seal low pressure outlet side pressure. The second parameter may be acquired in real time, and the leakage amount can be measured and calculated in real time by acquiring the second parameter in real time in specific applications.
Further, in an implementation, the second parameter is measured by the first sensor and the second sensor. Specifically, a first sensor is installed on the labyrinth seal high pressure inlet side to measure the labyrinth seal high pressure inlet side pressure; a second sensor is mounted on the low pressure outlet side of the labyrinth seal to measure the low pressure outlet side of the labyrinth seal.
S3, initializing and calculating the leakage quantity; that is, the leakage amount is initially calculated by the first parameter and the second parameter, and an initial amount is obtained.
In specific implementation, the initialized calculation formula of the leakage amount is as follows:
；
wherein,for the initial value of leakage->High pressure inlet side pressure for labyrinth seal, +.>Low pressure outlet side pressure for labyrinth seal, +.>The medium density is the labyrinth seal gap cross-sectional area.
；
Wherein,to seal the axial gap>Is the diameter of the rotating shaft.
And S4, carrying out iterative calculation on the leakage quantity until the calculation error is not larger than the setting error.
In particular implementations, each iterative calculation includes the steps of,
s41, calculating the Reynolds number, the turbulent energy conversion number and the flow coefficient of each sealing cavity according to the initialized calculated leakage amount or the updated leakage amount after the previous iterative calculation.
In particular, the leakage amount after the t labyrinth seal tooth is；
Wherein,the leakage quantity of the t sealing tooth belongs to a process value in calculation; />For medium density->Is->Flow coefficient of the individual sealed chambers, +.>For the pressure of the t-th seal chamber, +.>Is the pressure of t+1 sealed chambers. That is, the present formula is used to calculate the amount of labyrinth seal leakage between the t-th seal chamber and the t+1th seal chamber. In the embodiment, the t-th seal chamber refers to the t-th seal chamber in a direction from the high pressure side to the low pressure side.
The pressures before and after the labyrinth seal gap are calculated as follows:
,/>
wherein n is the number of teeth in the seal,for leakage, A is the labyrinth seal gap cross-sectional area.
Wherein,to seal the axial gap>Is the diameter of the rotating shaft.
In the present invention, the turbulent energy swivel coefficient takes into account the labyrinth seal geometry, as well as the dimensionless parameter Reynolds number Re that is capable of characterizing the fluid properties. The research shows that the relation between the turbulent energy transfer coefficient and the Reynolds number is consistent under the condition of different pressure ratios, and the method has good applicability under the working conditions of different pressure ratios. The first seal cavity flow coefficient is determined by the ratio of seal tooth width to seal tooth pitch and Reynolds number, and the remaining seal cavity flow coefficients are related to the turbulent energy swivel coefficient and the first seal cavity flow coefficient.
In particular, the method comprises the steps of,；
wherein,is Reynolds number (Reynolds number)>For the leakage of the seal tooth, +.>Is the diameter of the rotating shaft>Is dynamic viscosity.
The calculation formula of the turbulent kinetic energy rotating coefficient is as follows:
wherein,for the turbulent energy transformation coefficient, +.>To seal the axial gap>For sealing the tooth pitch->Is Reynolds number (Reynolds number)>Is the seal tooth width.
The flow coefficient calculation formula of the first seal cavity is as follows:
；
wherein,for the flow coefficient of the first sealed chamber, < >>To seal the axial gap>Is Reynolds number (Reynolds number)>Is the width of the seal teeth;
first, theThe flow coefficient calculation formula of each sealing cavity is as follows:
；
wherein,for the flow coefficient of the first sealed chamber, < >>Is->Flow coefficient of each sealed cavity.
In practice, the flow coefficients of the other sealed chambers are calculated based on the flow coefficient of the first sealed chamber.
S42, calculating the pressure of each sealing cavity by taking the pressure of the first sealing cavity as the pressure of the high pressure inlet and the pressure of the last sealing cavity as the pressure of the low pressure outlet of the labyrinth seal.
Specifically, the pressure of the high-pressure inlet side of the labyrinth seal is made to be the pressure of the first sealing cavity, the pressure of the low-pressure outlet side of the labyrinth seal is made to be the pressure of the last sealing cavity, and the pressure of each sealing cavity can be obtained by substituting the pressure into the labyrinth seal leakage amount calculation formula.
S43, calculating the leakage amount and calculation error of the last seal tooth. The leakage amount and calculation error of the last seal tooth can be calculated according to the leakage amount calculation formula. Specifically, the calculation error may be an error between the leakage amount of the most one seal tooth calculated in the current iteration and the previous iteration.
S44, judging whether to exit iterative computation, specifically, updating the leakage amount when the computation error is not less than the set error and the iteration number is not more than the set number; and when the calculation error is smaller than the set error, exiting the iterative calculation. In a specific implementation, the setting error may be 0.0001 and the iteration number may be 10000. Of course, in practical application, the setting error and the iteration number may be set as required, for example, the setting error is 0.0002, 0.0003, or 0.0004, and the iteration number may be set to 20000, 30000, or 40000, and the like. In the specific implementation, after the iteration times reach the set times, if the calculation error is still greater than the set error, the output is not converged, and the calculation process is exited.
The jth iteration calculates the error as follows:
the error meets the set requirement, and the method for updating the leakage quantity is that the calculated leakage quantity is updated as follows:
；
wherein,leakage amount calculated for the j-th iteration, < >>The leakage amount calculated for the j-1 th iteration.
S5, taking the leakage quantity of the last seal tooth of the last iteration as a final calculation result.
In the calculation of the invention, the turbulent energy turning coefficient considers the labyrinth seal geometric dimension and the dimensionless parameter Reynolds number Re which can characterize the fluid property. Because the relation between the turbulent kinetic energy turning coefficient and the Reynolds number is kept consistent under the condition of different pressure ratios, the method has good applicability under the working conditions of different pressure ratios. The first seal cavity flow coefficient is determined by the ratio of seal tooth width to seal tooth pitch and Reynolds number, and the remaining seal cavity flow coefficients are related to the turbulent energy swivel coefficient and the first seal cavity flow coefficient. Through the steps, the leakage amount of the labyrinth seal can be measured and calculated in real time.
In the specific implementation, the calculation process in a certain example is shown in table 1.
Table 1 turbine pump labyrinth seal leakage calculation example
Example 2
The present embodiment proposes a system for implementing the method of embodiment 1, and the same points can be referred to embodiment 1, and the details are not repeated herein, and only the differences will be described below.
Referring to fig. 5, the present embodiment provides a liquid rocket engine turbopump labyrinth seal leakage measurement system, which includes a first pressure sensor, a second pressure sensor, a parameter input module, a data storage module and a data operation module. In the implementation, the first pressure sensor and the second pressure sensor can acquire corresponding pressure values in real time, and the leakage amount can be detected in real time by using detection results of the first pressure sensor and the second pressure sensor.
In practice, referring to fig. 2 to 4, the first pressure sensor is installed at the labyrinth seal inlet; and the second pressure sensor is arranged at the outlet of the labyrinth seal.
The parameter input module is used for acquiring a first parameter. In the implementation, the first parameter may be preset according to specific conditions, or may be manually input by an operator. Specifically, the first parameters include geometric parameters and media parameters. Specifically, the first parameters include radial clearance, seal pitch, seal tooth width, shaft diameter, seal tooth count, fluid density, and hydrodynamic viscosity.
The data storage module is electrically connected with the first pressure sensor and the second pressure sensor; the data storage module is used for collecting the pressure at the labyrinth seal inlet through the first pressure sensor and collecting the pressure at the labyrinth seal outlet through the second pressure sensor.
When in implementation, the data storage module is used for storing data, and the stored data comprises a first parameter, a second parameter and a data operation result.
The data operation module is electrically connected with the data storage module; the data operation module is used for acquiring the first parameter, the detection result of the first pressure sensor and the detection result of the second pressure sensor through the data storage module to calculate leakage. That is, the method in embodiment 1 is performed by the data operation module according to the first parameter and the second parameter.
In specific implementation, the data operation module is used for performing iterative computation according to a labyrinth seal leakage amount calculation formula, a Reynolds number calculation formula, a turbulence energy turning coefficient calculation formula and a flow coefficient calculation formula of each sealing cavity so as to obtain the final labyrinth seal leakage amount. Specifically, the process of performing iterative computation by the data operation module and the corresponding computation formula can refer to embodiment 1.
In particular, in order to facilitate the checking of the calculation process and the result, the system further comprises a data display module electrically connected with the data storage module for displaying the parameter values and the final calculation result in the calculation process.
While the foregoing is directed to embodiments of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.
Claims (4)
1. A method for measuring leakage of a labyrinth seal of a turbopump of a liquid rocket engine is characterized by comprising the steps of,
acquiring a first parameter; the first parameters include radial clearance, seal tooth pitch, seal tooth width, shaft diameter, seal tooth number, fluid density, and hydrodynamic viscosity;
collecting a second parameter; the second parameter includes a labyrinth seal high pressure inlet side pressure and a labyrinth seal low pressure outlet side pressure;
initializing and calculating leakage quantity; the initialized calculation formula of the leakage amount is as follows:
；
wherein,for the initial value of leakage->High pressure inlet side pressure for labyrinth seal, +.>Low pressure outlet side pressure for labyrinth seal, +.>The density of the medium is that A is the cross section area of the labyrinth seal gap;
；
wherein,to seal the axial gap>The diameter of the rotating shaft;
performing iterative calculation on the leakage quantity until the calculation error is not larger than the set error;
taking the result of the last iteration as a final calculation result;
each iterative calculation comprises the following steps,
calculating the Reynolds number, the turbulent kinetic energy transfer number and the flow coefficient of each sealing cavity according to the initialized calculated leakage amount or the updated leakage amount after the previous iterative calculation;
taking the pressure of the first sealing cavity as the high-pressure inlet side pressure of the labyrinth seal, taking the pressure of the last sealing cavity as the low-pressure outlet side pressure of the labyrinth seal, and calculating the pressure of each sealing cavity;
calculating the leakage quantity and calculation error of the last seal tooth;
updating the leakage amount when the calculation error is not smaller than the set error and the iteration number is not larger than the set number; when the calculation error is smaller than the set error, the iterative calculation is stopped;
in the iterative calculation, the calculation formula of the Reynolds number is:
；
wherein,is Reynolds number (Reynolds number)>For leakage amount->Is the diameter of the rotating shaft>Is dynamic viscosity;
in iterative computation, the computation formula of the turbulent energy transfer coefficient is as follows:
wherein,for the turbulent energy transformation coefficient, +.>To seal the axial gap>For sealing the tooth pitch->Is Reynolds number (Reynolds number)>Is the width of the seal teeth;
in the iterative calculation process, the flow coefficient calculation formula of the first sealed cavity is as follows:
；
wherein,for the flow coefficient of the first sealed chamber, < >>To seal the axial gap>Is Reynolds number (Reynolds number)>Is the width of the seal teeth;
first, theThe flow coefficient calculation formula of each sealing cavity is as follows:
；
wherein,for the flow coefficient of the first sealed chamber, < >>Is->Flow coefficients of the seal chambers;
the pressures before and after the labyrinth seal gap are calculated as follows:
,/>
wherein n is the number of teeth in the seal,the leakage quantity is A, and the sectional area of the labyrinth seal gap is A;
the j-th iterative calculation error is as follows:
the error meets the set requirement, and the method for updating the leakage quantity is that the calculated leakage quantity is updated as follows:
；
wherein,leakage amount calculated for the j-th iteration, < >>The leakage amount calculated for the j-1 th iteration.
2. A liquid rocket engine turbopump labyrinth seal leakage measurement system for use in the method of claim 1, comprising,
the first pressure sensor is arranged at the labyrinth seal inlet;
the second pressure sensor is arranged at the labyrinth seal outlet;
the parameter input module is used for acquiring a first parameter;
the data storage module is electrically connected with the first pressure sensor and the second pressure sensor; the data storage module is used for collecting the pressure at the labyrinth seal inlet through the first pressure sensor and collecting the pressure at the labyrinth seal outlet through the second pressure sensor;
the data operation module is electrically connected with the data storage module; the data operation module is used for acquiring the first parameter, the detection result of the first pressure sensor and the detection result of the second pressure sensor through the data storage module to calculate leakage.
3. The liquid rocket engine turbopump labyrinth seal leakage amount calculation system according to claim 2, wherein the data operation module is configured to perform iterative calculation according to a labyrinth seal leakage amount calculation formula, a reynolds number calculation formula, a turbulent energy swivel coefficient calculation formula, and a flow coefficient calculation formula of each seal cavity, so as to obtain a final labyrinth seal leakage amount.
4. The liquid rocket engine turbopump labyrinth seal leakage amount calculation system of claim 2, further comprising a data display module electrically connected to the data storage module for displaying parameter values in the calculation process and final calculation results.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311352292.0A CN117094252B (en) | 2023-10-19 | 2023-10-19 | Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311352292.0A CN117094252B (en) | 2023-10-19 | 2023-10-19 | Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117094252A CN117094252A (en) | 2023-11-21 |
| CN117094252B true CN117094252B (en) | 2023-12-29 |
Family
ID=88777622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311352292.0A Active CN117094252B (en) | 2023-10-19 | 2023-10-19 | Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117094252B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104471293A (en) * | 2012-04-27 | 2015-03-25 | 诺沃皮尼奥内股份有限公司 | High damping labyrinth seal with helicoidal or helicoidal-cylindrical mixed pattern |
| CN108710750A (en) * | 2018-05-17 | 2018-10-26 | 沈阳工业大学 | Stepped tooth labyrinth seal structure parameters optimization method |
| CN109359430A (en) * | 2018-11-29 | 2019-02-19 | 上海交通大学 | Vertical long shaft pump clearance seal calculation method |
-
2023
- 2023-10-19 CN CN202311352292.0A patent/CN117094252B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104471293A (en) * | 2012-04-27 | 2015-03-25 | 诺沃皮尼奥内股份有限公司 | High damping labyrinth seal with helicoidal or helicoidal-cylindrical mixed pattern |
| CN108710750A (en) * | 2018-05-17 | 2018-10-26 | 沈阳工业大学 | Stepped tooth labyrinth seal structure parameters optimization method |
| CN109359430A (en) * | 2018-11-29 | 2019-02-19 | 上海交通大学 | Vertical long shaft pump clearance seal calculation method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117094252A (en) | 2023-11-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Clark et al. | Effects of purge flow configuration on sealing effectiveness in a rotor–stator cavity | |
| Cooper | Analysis of single-and two-phase flows in turbopump inducers | |
| Beard et al. | Effect of combustor swirl on transonic high pressure turbine efficiency | |
| Serrano et al. | Importance of mechanical losses modeling in the performance prediction of radial turbochargers under pulsating flow conditions | |
| Braun et al. | Design and experimental assessment of bladeless turbines for axial inlet supersonic flows | |
| Kochrad et al. | System-level performance of microturbines with an inside-out ceramic turbine | |
| Aghaali et al. | Turbocharged si-engine simulation with cold and hot-measured turbocharger performance maps | |
| CN117094252B (en) | Liquid rocket engine turbopump labyrinth seal leakage amount measuring method and system | |
| Cho et al. | Design, flow simulation, and performance test for a partial-admission axial turbine under supercritical CO2 condition | |
| Barsi et al. | Analysis of the loss production mechanism due to cavity–main flow interaction in a low-pressure turbine stage | |
| Wang et al. | Development and verification of helium–xenon mixture cooled small reaction system | |
| Pelz et al. | Efficiency scaling: influence of Reynolds and Mach numbers on fan performance | |
| Kuznetsov et al. | Experimental and calculation study of diesel-generator performance in transient conditions | |
| Schein et al. | Scroll compressor simulation model | |
| Khalil et al. | Experimental and numerical investigation of blade height effects on micro-scale axial turbines performance using compressed air open cycle | |
| Sakellaridis et al. | Meanline modeling of radial turbine performance for turbocharger simulation and diagnostic applications | |
| Mataczynski et al. | Design and testing of a small pressure wave supercharger for an industrial diesel engine | |
| Serrano et al. | Methodology to evaluate turbocharger turbine performance at high blade to jet speed ratio under quasi adiabatic conditions | |
| Huber et al. | Design and test of a small two stage counter-rotating turbine for rocket engine application | |
| CN110657124B (en) | Method and system for acquiring friction temperature rise condition in end face sealing structure | |
| Guo et al. | Efficient modeling of an axial compressor with swirl distortion | |
| Zhang et al. | Study on similitude method for turbine considering working fluid physical properties variation | |
| Galindo et al. | Assessment of a twin-entry turbine efficiency model including momentum exchange between branches | |
| Castner et al. | An engine research program focused on low pressure turbine aerodynamic performance | |
| Yu et al. | Experimental Study on the Effect of High-Pressure Inflow on the Performance of Wankel Pump: Exploration of the Gravity-Pump Pressure Collaborative Dynamic Loading Method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |