CN109711047B - Design method for aerodynamic performance of S2 flow surface of helium compressor - Google Patents
Design method for aerodynamic performance of S2 flow surface of helium compressor Download PDFInfo
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Abstract
A design method for S2 flow surface aerodynamics of a helium compressor belongs to the technical field of compressor aerodynamic design. The invention solves the problem of poor performance of the helium compressor in the conventional S2 flow surface pneumatic design. The total adiabatic power adding amount of each stage of the helium compressor is reasonably designed and reasonably distributed, the total pressure ratio, adiabatic power and power consumption of the helium compressor are obtained by calculating the temperature rise of each stage, the total helium temperature before each stage, the pressure ratio of each stage and the total pressure before each stage of the helium compressor, and the geometric size of the first stage and the geometric size of the last stage of uniform diameter pneumatic operation of the helium compressor are determined to complete the design of the same flow size; and designing by adopting an equal-circular-quantity twisting rule along the diameter to complete the aerodynamic design of the S2 flow surface. The method can be applied to the technical field of pneumatic design of the helium gas compressor.
Description
Technical Field
The invention belongs to the technical field of pneumatic design of a gas compressor, and particularly relates to a design method for S2 flow surface aerodynamics of a helium gas compressor.
Background
Aerodynamic calculation of the flow surface of the helium compressor S2 generally adopts a streamline curvature method to solve a complete radial balance equation on an average flow surface of S2. The initial aerodynamic design calculation of the flow surface of the compressor S2 adopts a simplified radial balance equation which ignores the streamline gradient and the streamline curvature to obtain the speed triangle required by the blade design, and the method plays a basic role in the design of the compressor with low pressure ratio. A complete radial balance equation and an S2 flow surface theory which take the influence of the streamline gradient and the streamline curvature into consideration are developed later, so that the design calculation result of the compressor is more accurate, and particularly, the performance of the helium compressor is improved to a certain extent by aiming at the calculation of transonic flow. However, the existing S2 flow surface aerodynamic design solving method is completed under a simplified equation neglecting the influence of the airflow viscosity, so the existing S2 flow surface aerodynamic design method has a limited effect of improving the performance of the helium compressor, that is, the performance of the helium compressor is still poor.
Disclosure of Invention
The invention aims to solve the problem of poor performance of a helium compressor with an existing S2 flow surface aerodynamic design.
The technical scheme adopted by the invention for solving the technical problems is as follows: a design method for the aerodynamic performance of a flow surface S2 of a helium compressor comprises the following steps:
step one, utilizing the through-flow pressure ratio of a helium gas compressor
Calculating the sum of all levels of adiabatic power adding amount of the helium compressor and reasonably distributing;
step two: determining the stage number of the helium gas compressor, calculating the temperature rise of each stage, the total helium gas temperature before each stage, the pressure ratio of each stage and the total pressure before each stage of the helium gas compressor, and calculating the total pressure ratio, the adiabatic power and the power consumption power of the helium gas compressor;
step three: calculating the pneumatic first-stage geometric dimension and final-stage geometric dimension of the helium compressor along the mean diameter;
step four: obtaining the through-flow size of the helium compressor through the parameters determined in the first step to the third step;
step five: the pneumatic design of the flow surface of the helium compressor S2 adopts an equal-circulation-quantity twisting rule along the diameter;
step six: and (4) setting the efficiency and loss distribution of the airflow along the blade height according to an empirical model by using the calculation results of the first step to the fifth step, and realizing the aerodynamic design of the flow surface of the helium compressor S2.
The invention has the beneficial effects that: the invention provides a design method for S2 flow surface pneumatics of a helium compressor, which comprises the steps of reasonably designing the sum of all levels of adiabatic work addition amount of the helium compressor and reasonably distributing the sum, calculating all levels of temperature rise, total helium temperature before all levels, all levels of pressure ratio and total pressure before all levels of the helium compressor to obtain the total pressure ratio, adiabatic power and power consumption of the helium compressor, and determining the first-level geometric dimension and the last-level geometric dimension of the helium compressor along the mean diameter pneumatics to further complete the design of the same flow dimension; the design is carried out by adopting an equal-ring-quantity distortion rule along the diameter, the aerodynamic design of the S2 flow surface is completed, and compared with the existing method, the design method provided by the invention can be used for well improving the performance of the helium compressor.
Drawings
FIG. 1 is a flow chart of a design method for flow surface aerodynamics of a helium compressor S2 of the invention;
Detailed Description
The first embodiment is as follows: as shown in fig. 1, the design method for aerodynamic performance of a flow surface of a helium compressor S2 according to the present embodiment includes the following steps:
step one, utilizing the through-flow pressure ratio of a helium gas compressor
Calculating the sum of all levels of adiabatic power adding amount of the helium compressor, and reasonably distributing;
step two: determining the stage number of the helium gas compressor, calculating the temperature rise of each stage, the total helium gas temperature before each stage, the pressure ratio of each stage and the total pressure before each stage of the helium gas compressor, and calculating the total pressure ratio, the adiabatic power and the power consumption power of the helium gas compressor;
step three: calculating the pneumatic first-stage geometric dimension and final-stage geometric dimension of the helium compressor along the mean diameter;
step four: obtaining the through-flow size of the helium compressor through the parameters determined in the first step to the third step;
step five: the pneumatic design of the flow surface of the helium compressor S2 adopts an equal-circulation-quantity twisting rule along the diameter;
step six: and (4) setting the efficiency and loss distribution of the airflow along the blade height according to an empirical model by using the calculation results of the first step to the fifth step, and realizing the aerodynamic design of the flow surface of the helium compressor S2.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: the specific process of the step one is as follows:
the pressure of the air flow at the beginning of the inlet section is
The pressure of the gas stream as it passes through the end of the outlet section is
According to
And
calculating the through-flow pressure ratio of the helium compressor
Through-flow pressure ratio of helium compressor
Calculating adiabatic power H of helium compressor 0 ：
Wherein H 0 The adiabatic power adding quantity of the helium compressor is obtained, k is an adiabatic index, and R is a gas constant;
the sum sigma h of adiabatic power addition of each stage of the helium gas compressor 0 Comprises the following steps:
wherein eta i In order to achieve a level of average efficiency,
the heat insulation efficiency of the helium compressor is improved.
The third concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the accessory conditions of the equal ring magnitude distortion rule are as follows: the axial velocity of the airflow is constant along the blade height.
The fourth concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the motion of the air flow with the equal-circulation twisting law comprises translation, deformation and rotation motion;
the rotation motion is expressed by the rotation of the airflow micro-group around the self axis, and the expression form of the airflow vorticity under a cylindrical coordinate system is obtained according to the rotation angular velocity omega of the airflow;
according to the simplified radial balance requirement and the accessory condition of equal ring volume level, the vorticity and the angular speed of the obtained air flow are both zero;
the air flow is unchanged along the radial processing amount, the tangential speed of the air flow is reduced along with the increase of the radius of the blade height, and the axial speed of the air flow is unchanged along the blade height;
making a speed triangle according to the change rule of the speed and the angle of each airflow around the movable blade along the radius of the blade height, and obtaining the change condition of the speed triangle along the radius of the blade height;
the reaction degree is increased along with the increase of the radius of the blade height, namely the reaction degree at the blade tip is the largest, and the reaction degree at the blade root is the smallest;
the flow coefficient is reduced along with the increase of the radius of the blade height, namely the flow coefficient at the blade tip is minimum, and the flow coefficient at the blade root is maximum;
the energy head coefficient decreases with increasing radius of the blade height.
The fifth concrete implementation mode: the first difference between the present embodiment and the specific embodiment is: the specific process of the second step is as follows:
determining the stage number of the helium compressor, and calculating the pneumatic parameters of each stage:
ith stage heating of helium compressor
Comprises the following steps:
in the formula: h is s，i Is the i-th adiabatic working amount, η s，i I is the ith grade of adiabatic efficiency, i is the grade number;
total temperature of helium before ith stage of helium compressor
To, where the first level is given according to design requirements:
ith stage pressure ratio of helium compressor
Comprises the following steps:
no. i front total pressure of helium compressor
To, where the top level is given according to design requirements:
in the formula:
representing the total pressure before the i-1 stage;
total pressure ratio of helium compressor
Comprises the following steps:
adiabatic efficiency of helium compressor
Comprises the following steps:
in the formula:
showing the total temperature of helium before 1 stage of the helium compressor,
representing the total temperature of a final stage helium outlet of the helium compressor;
power consumption N of helium compressor e Comprises the following steps:
in the formula: g represents the flow rate of the helium gas,
indicates the total temperature rise, eta, of helium m Indicating the mechanical efficiency of the helium compressor.
The sixth specific implementation mode: the first difference between the present embodiment and the specific embodiment is: the concrete process of the third step is as follows:
calculating the pneumatic first-stage geometric dimension of the helium compressor along the uniform diameter:
the axial speed of an inlet at the position of the first stage of uniform diameter is C 1a The peripheral speed at the outer diameter of the first stage movable blade is U 1t D 'hub ratio at primary inlet' 1 Calculating the geometric dimension of the first-stage diameter-equalizing;
in the formula: d t1 The outer diameter of the first-stage movable blade is defined, and n is the rotating speed of a helium compressor;
in the formula: f 1 Is the inlet flow area;
in the formula: k is a radical of m As flow reserve coefficient, ρ 1 The static density of the inlet of the compressor;
in the formula: d h1 The inner diameter of the first stage movable blade;
first stage moving blade height, i.e. first stage geometry L, of helium gas compressor 1 Comprises the following steps:
calculating the final geometrical size of the helium compressor along the mean diameter aerodynamics:
hub diameter D of final stage outlet hz ＝D h1 Axial outlet velocity of C za ；
In the formula: f z Is the outlet flow area, rho, of the helium compressor z The static density of an outlet of a helium compressor;
in the formula: d tz The outer diameter of the final outlet;
the total pressure loss coefficient of the last stage outlet straightening vane is taken as Zeta o Then total pressure at the outlet
Comprises the following steps:
static temperature T of outlet of helium gas compressor z Comprises the following steps:
in the formula:
is the total temperature of the outlet of the helium compressor C p Is constant pressure specific heat;
static pressure P at outlet of helium compressor z Comprises the following steps:
static density rho of airflow at outlet of helium compressor z Comprises the following steps:
helium compressor outlet hub ratio d' z Comprises the following steps:
final tip height, i.e. final geometry L, of helium gas compressor z Comprises the following steps:
the above-described calculation examples of the present invention are merely to explain the calculation model and the calculation flow of the present invention in detail, and are not intended to limit the embodiments of the present invention. It will be apparent to those skilled in the art that other variations and modifications of the present invention can be made based on the above description, and it is not intended to be exhaustive or to limit the invention to the precise form disclosed, and all such modifications and variations are possible and contemplated as falling within the scope of the invention.
Claims (3)
1. A design method for aerodynamics of a flow surface of a helium compressor S2 is characterized by comprising the following steps:
step one, utilizing the through-flow pressure ratio of a helium gas compressor
Calculating the sum of all levels of adiabatic power addition of the helium compressor;
the specific process of the step one is as follows:
through-flow pressure ratio of helium compressor
Calculating adiabatic power H of helium compressor 0 ：
Wherein H 0 The adiabatic work adding quantity of the helium compressor, k is an adiabatic index, R is a gas constant,
represents the total intake air temperature;
the sum sigma h of adiabatic power addition of each stage of the helium gas compressor 0 Comprises the following steps:
wherein eta is i In order to achieve a level of average efficiency,
the heat insulation efficiency of the helium compressor is improved;
step two: determining the stage number of the helium gas compressor, calculating the temperature rise of each stage, the total helium temperature before each stage, the pressure ratio of each stage and the total pressure before each stage of the helium gas compressor, and calculating the total pressure ratio, the adiabatic power and the power consumption power of the helium gas compressor;
the specific process of the second step is as follows:
determining the stage number of the helium gas compressor, and calculating the pneumatic parameters of each stage:
ith stage heating of helium compressor
Comprises the following steps:
in the formula: h is s,i Is the i-th adiabatic working amount, η s,i I is the stage number;
total temperature of helium before ith stage of helium compressor
Comprises the following steps:
in the formula (I), the compound is shown in the specification,
the total temperature of helium gas before the i-1 st stage of the helium gas compressor,
heating the ith-1 stage of the helium compressor;
ith stage pressure ratio of helium compressor
Comprises the following steps:
no. i front total pressure of helium compressor
Comprises the following steps:
in the formula:
representing the total pressure before the i-1 stage;
total pressure ratio of helium compressor
Comprises the following steps:
in the formula (I), the compound is shown in the specification,
the pressure of the gas stream as it passes through the end of the outlet section,
the pressure of the air flow when the air flow passes through the initial end of the inlet section;
adiabatic efficiency of helium compressor
Comprises the following steps:
in the formula:
showing the total temperature of helium gas before 1 stage of the helium gas compressor,
representing the final stage helium outlet total temperature of the helium compressor;
power consumption N of helium compressor e Comprises the following steps:
in the formula: g represents the flow rate of the helium gas,
indicates the total temperature rise, eta, of helium m Indicating the mechanical efficiency of the helium compressor;
step three: calculating the pneumatic first-stage geometric dimension and final-stage geometric dimension of the helium compressor along the mean diameter;
the specific process of the third step is as follows:
first stage moving blade height, i.e. first stage geometry L, of helium gas compressor 1 Comprises the following steps:
in the formula, D h1 Is the first stage moving blade inner diameter, D t1 The outer diameter of the first stage movable blade;
final tip height, i.e. final geometry L, of helium gas compressor z Comprises the following steps:
in the formula, D tz Is the final stage outlet outer diameter, D hz The hub diameter at the final stage exit;
step four: obtaining the through-flow size of the helium gas compressor through the parameters determined in the first step to the third step;
step five: the pneumatic design of the flow surface of the helium compressor S2 adopts an equal-circulation-quantity twisting rule along the diameter;
step six: and (4) realizing the pneumatic design of the flow surface of the helium compressor S2 according to the efficiency and loss distribution of the airflow along the blade height by using the calculation results of the first step to the fifth step.
2. The design method for aerodynamics of the flow surface of S2 of the helium compressor of claim 1, wherein the accessory conditions of the equal annular magnitude twist law are as follows: the axial velocity of the air flow is constant along the blade height.
3. The design method for aerodynamic design of the flow surface of the helium compressor S2 as claimed in claim 1, wherein the motion of the air flow with the equal-ring-quantity twist law comprises translation, deformation and rotation motion;
the rotation motion is expressed by the rotation of the airflow micro-group around the self axis, and the expression form of the airflow vorticity under a cylindrical coordinate system is obtained according to the rotation angular velocity omega of the airflow;
according to the simplified radial balance requirement and the accessory condition of equal ring volume level, the vorticity and the angular speed of the obtained air flow are both zero;
the air flow is unchanged along the radial processing amount, the tangential speed of the air flow is reduced along with the increase of the radius of the blade height, and the axial speed of the air flow is unchanged along the blade height;
making a speed triangle according to the change rule of the speed and the angle of each air flow in front of and behind the movable blade along the blade height radius, and obtaining the change condition of the speed triangle along the blade height radius;
the reaction degree is increased along with the increase of the radius of the blade height, namely the reaction degree at the blade tip is the largest, and the reaction degree at the blade root is the smallest;
the flow coefficient is reduced along with the increase of the radius of the blade height, namely the flow coefficient at the blade tip is minimum, and the flow coefficient at the blade root is maximum;
the energy head coefficient decreases with increasing radius of the blade height.
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| CN106122062A (en) * | 2016-05-31 | 2016-11-16 | 哈尔滨工程大学 | A kind of utilize the prediction of Capability of Compressor that supercritical carbon dioxide fluid is working medium and appraisal procedure |
| CN107679270A (en) * | 2017-08-28 | 2018-02-09 | 西北工业大学 | Centrifugal compressor Optimization Design and system |
| CN108710746A (en) * | 2018-02-08 | 2018-10-26 | 哈尔滨广瀚燃气轮机有限公司 | Take into account the anti-twisted design method that naval vessel combustion engine compressor blade and blade predeformation influences |
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