CN117951831A - One-dimensional inverse problem design method for guide vane-free staggered counter-rotating turbine - Google Patents
One-dimensional inverse problem design method for guide vane-free staggered counter-rotating turbine Download PDFInfo
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Abstract
The invention provides a one-dimensional inverse problem design method of a guide vane-free staggered counter-rotating turbine, which comprises the steps of 1) establishing a method for calculating the inlet and outlet peripheral speeds of a kth stage movable vane based on the design radius, high-pressure and low-pressure shaft rotating speeds in an inlet vane of the turbine, the total rim work of the turbine, the work distribution coefficients of a 1 st stage turbine to a kth stage turbine and the loading coefficients of the 1 st stage turbine to the kth stage turbine; 2) Establishing a method for calculating the axial speed of the inlet and the outlet of the k-th stage movable blade based on the absolute speed of the inlet of the turbine, the airflow angle of the inlet of the turbine, the circumferential speeds of the inlet and the outlet of the 1-th stage movable blade to the k-th stage movable blade and the flow coefficients of the 1-th stage to the k-th stage; 3) The method for calculating the circumferential speeds of the inlet and the outlet of the k-th stage movable blade based on the absolute speed of the inlet of the turbine, the airflow angle of the inlet of the turbine, the total rim work of the turbine, the circumferential speeds of the inlet and the outlet of the 1-th stage movable blade to the k-th stage movable blade and the work distribution coefficients of the 1-th stage turbine to the k-th stage turbine is established. The invention realizes one-dimensional design calculation for the guide vane-free staggered counter-rotating turbine.
Description
Technical Field
The invention provides a one-dimensional inverse problem design method for a guide vane-free staggered counter-rotating turbine, and belongs to the technical field of turbine design.
Background
The turbine is a high Wen Reduan part of an aero-engine, the design of the turbine relates to various technologies such as air-driving, cooling, structural strength, materials, processes and the like, and the research on the turbine is one of main obstacles for preventing the development of aero-power technology in China. One trend in turbine development is the weight reduction of engines, requiring turbine ends to adopt the structural form of each stage of high and low pressure turbines as much as possible, even eliminating guide vanes. Such turbines are commonly referred to as counter-rotating turbines.
Counter-rotating turbines (CRTs, counter rotating turbines) refer to adjacent two-stage rotors in a multi-stage rotor turbine that are opposite in rotation direction, and in practical applications, the counter-rotating turbines can be divided into a vaned counter-rotating turbine and a vaneless counter-rotating turbine. While conventional counter-rotating turbine designs such as 1+1, 1+1/2 and the like have more mature design methods, the one-dimensional inverse problem design of the multi-stage guide vane-free staggered counter-rotating turbine is not researched at present.
Disclosure of Invention
Aiming at the technical problems, the invention provides a one-dimensional inverse problem design method of a guide vane-free staggered counter-rotating turbine, which can rapidly design a one-dimensional meridian runner of a multi-stage guide vane-free counter-rotating turbine.
Based on the above relation, the one-dimensional inverse problem design method of the guide vane-free staggered counter-rotating turbine comprises the following steps:
S1, obtaining boundary conditions and stage design parameters of a guide vane-free staggered counter-rotating turbine;
S2, preprocessing data of the turbine, and calculating parameters which can be quickly obtained according to input conditions, including turbine inlet parameter calculation and the like;
S3, obtaining an initial turbine stage expansion ratio according to the work distribution coefficient, calculating the isentropic work of the stage according to the stage expansion ratio, and enabling the rim work to be the same as the isentropic work. In the following formula, the superscript i represents the turbine stage number, and L ad represents the turbine isentropic work:
S4, calculating a turbine stage speed triangle according to a speed triangle calculation method of the guide vane-free staggered counter-rotating turbine;
s5, calculating the relative parameters of the high-pressure shaft and the low-pressure shaft of the cross section between the staggered opposite rotating blades;
s6, calculating geometric parameters of the staggered counter-rotating turbine by using an empirical formula, and simultaneously calculating total pressure loss of blades of the turbine;
S7, calculating new absolute total temperature of the outlet based on the absolute total pressure of the given outlet section through an entropy equation, and calculating total pressure loss of the movable blade;
s8, calculating rim work of a turbine stage of the guide vane-free staggered counter-rotating turbine;
S9, according to the fact that whether the calculated power distribution coefficients of all turbine stages are the same as the power distribution coefficients of all stages required by design or not. If not, the process proceeds to step S10, and the process proceeds to step S11;
s10, updating expansion ratios of all levels according to the ratio of the required power distribution coefficient to the calculated power distribution coefficient, and entering S4 when the expansion ratio product of all levels is consistent with the total expansion ratio;
S11, calculating and outputting one-dimensional parameters of the guide vane-free staggered counter-rotating turbine. Compared with a conventional axial flow turbine, the method reduces the number of dimensionless design parameters by establishing the speed triangle of the guide vane-free counter-rotating turbine, and realizes the relationship between the turbine stage speed triangle and the design parameters by only using the two dimensionless design parameters, namely the load coefficient and the flow coefficient, thereby realizing the establishment of the guide vane-free counter-rotating turbine speed triangle.
Compared with a conventional axial flow turbine, the guide vane-less staggered counter-rotating turbine is characterized by the existence of no guide vanes, and the dimensionless design parameters are much smaller in number compared with the conventional turbine, so the required design parameters are as follows:
total design parameters: turbine inlet total temperature T t, turbine inlet total pressure P t, turbine inlet Mach number Ma, turbine inlet airflow angle alpha 1, turbine design flow G, turbine design expansion ratio pi, turbine inlet vane design radius R 1, high pressure shaft rotational speed N 1, low pressure shaft rotational speed N 2, high pressure shaft series S 1, low pressure shaft series S 2.
Stage design parameters: work distribution coefficient omega, load coefficient mu, flow coefficientLoss model dependent parameters
Wherein, in the stage design parameters, the load coefficient and the flow coefficient are the dimensionless design parameters of the turbine, compared with the conventional turbine, the load coefficient mu is defined as follows:
Wherein U 1 and U 2 are the peripheral speeds of the inlet and outlet of the movable blade, L u is the rim work and is generally composed of speeds, and the definition of the speeds is expressed as L below u＝C1uU1+C2uU2
Wherein, C 1u and C 2u are the absolute circumferential speeds of the inlet and the outlet of the movable blade.
Flow coefficientThe definition formula is as follows:
Wherein, C 1a and C 2a are the absolute axial speeds of the inlet and the outlet of the movable blade.
A one-dimensional inverse problem design method of a guide vane-free staggered counter-rotating turbine comprises the following steps: the relation between the circumferential speed, the axial speed and the circumferential speed of the turbine stage and the total parameters and the stage design parameters is established, and the design method is as follows:
1) Establishing a design radius R 1, high-pressure and low-pressure shaft rotating speeds N 1 and N 2, total rim work L u, work distribution coefficients omega 1～ωi of the 1 st-k-stage turbines and loading coefficients mu 1～μk of the 1 st-k-stage turbines in turbine inlet blades to calculate inlet and outlet peripheral speeds of the k-stage movable blades And/>Is a method of (2);
2) Establishing inlet and outlet peripheral speeds of the turbine inlet based on the absolute speed C 1 of the turbine inlet, the air flow angle alpha 1 of the turbine inlet and the turbine from the 1 st stage to the k th stage And/>Flow coefficient of 1 st to kth stage/>Calculating the axial velocity/>, of the inlet and outlet of the k-th stage movable bladeAnd/>Is a method of (2);
3) Establishing the turbine total rim work L u and the inlet and outlet peripheral speeds of the 1 st-kth-stage moving blades based on the absolute turbine inlet speed C 1 and the turbine inlet air flow angle alpha 1 And/>Work distribution coefficients omega 1～ωi of the 1 st-k-stage turbines calculate circumferential speeds/>, of inlet and outlet of k-stage movable bladesAnd/>Is a method of (2);
The method can calculate the speed triangle of each stage of the guide vane-free staggered counter-rotating turbine, and the speed triangle can determine the meridian flow passage of the turbine, so that one-dimensional design calculation of the guide vane-free staggered counter-rotating turbine is realized.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a schematic view of a four-stage vaneless staggered counter-rotating turbine meridian flow passage;
FIG. 3 is a schematic diagram of a four-stage vaneless staggered counter-rotating turbine speed triangle.
Detailed Description
The specific technical scheme of the invention is described with reference to the accompanying drawings and the embodiments.
The one-dimensional inverse problem design method of the guide vane-free staggered counter-rotating turbine, as shown in fig. 1, comprises the following steps:
S1, obtaining boundary conditions and stage design parameters of a guide vane-free staggered counter-rotating turbine;
S2, preprocessing data of the turbine, and calculating parameters which can be quickly obtained according to input conditions, including turbine inlet parameter calculation and the like;
S3, obtaining an initial turbine stage expansion ratio according to the work distribution coefficient, calculating the isentropic work of the stage according to the stage expansion ratio, and enabling the rim work to be the same as the isentropic work. In the following formula, the superscript i represents the turbine stage number, and L ad represents the turbine isentropic work:
S4, calculating a turbine stage speed triangle according to a speed triangle calculation method of the guide vane-free staggered counter-rotating turbine;
s5, calculating the relative parameters of the high-pressure shaft and the low-pressure shaft of the cross section between the staggered opposite rotating blades;
s6, calculating geometric parameters of the staggered counter-rotating turbine by using an empirical formula, and simultaneously calculating total pressure loss of blades of the turbine;
S7, calculating new absolute total temperature of the outlet based on the absolute total pressure of the given outlet section through an entropy equation, and calculating total pressure loss of the movable blade;
s8, calculating rim work of a turbine stage of the guide vane-free staggered counter-rotating turbine;
S9, according to the fact that whether the calculated power distribution coefficients of all turbine stages are the same as the power distribution coefficients of all stages required by design or not. If not, the process proceeds to step S10, and the process proceeds to step S11;
s10, updating expansion ratios of all levels according to the ratio of the required power distribution coefficient to the calculated power distribution coefficient, and entering S4 when the expansion ratio product of all levels is consistent with the total expansion ratio;
S11, calculating and outputting one-dimensional parameters of the guide vane-free staggered counter-rotating turbine. According to the above method, a four-stage vaneless staggered counter-rotating turbine can be designed, in fig. 2, the first and third rows of blades are mounted on the high pressure shaft (Blade 1 and Blade 3), and the second and fourth rows are mounted on the low pressure shaft (Blade 2 and Blade 4), both being blades. It can be seen from fig. 3 that the opposite-rotation turbine speed triangle is characterized in that the outlet absolute speed C 2 in fig. 3 (a) is consistent with the inlet absolute speed C 1 in fig. 3 (b) in the magnitude direction, and the first and third row of blade circumferential speeds U are opposite (opposite rotation) to the second and fourth row of blade circumferential speeds U due to no guide vane intervention.
Claims (2)
1. The one-dimensional inverse problem design method of the guide vane-free staggered counter-rotating turbine is characterized by comprising the following steps of:
S1, obtaining boundary conditions and stage design parameters of a guide vane-free staggered counter-rotating turbine;
s2, preprocessing data of the turbine, and calculating parameters which can be quickly obtained according to input conditions, including turbine inlet parameter calculation;
s3, obtaining an initial turbine stage expansion ratio according to the work distribution coefficient, calculating stage isentropic work according to the stage expansion ratio, and enabling the rim work to be the same as the isentropic work; in the following formula, the superscript i represents the turbine stage number, and L ad represents the turbine isentropic work:
S4, calculating a turbine stage speed triangle according to a speed triangle calculation method of the guide vane-free staggered counter-rotating turbine;
s5, calculating the relative parameters of the high-pressure shaft and the low-pressure shaft of the cross section between the staggered opposite rotating blades;
s6, calculating geometric parameters of the staggered counter-rotating turbine by using an empirical formula, and simultaneously calculating total pressure loss of blades of the turbine;
S7, calculating new absolute total temperature of the outlet based on the absolute total pressure of the given outlet section through an entropy equation, and calculating total pressure loss of the movable blade;
s8, calculating rim work of a turbine stage of the guide vane-free staggered counter-rotating turbine;
S9, according to the fact that whether the calculated power distribution coefficients of all turbine stages are identical to the power distribution coefficients of all stages required by design or not; if not, the process proceeds to step S10, and the process proceeds to step S11;
s10, updating expansion ratios of all levels according to the ratio of the required power distribution coefficient to the calculated power distribution coefficient, and entering S4 when the expansion ratio product of all levels is consistent with the total expansion ratio;
S11, calculating and outputting one-dimensional parameters of the guide vane-free staggered counter-rotating turbine.
2. The method for designing the one-dimensional inverse problem of the guide vane-less staggered counter-rotating turbine according to claim 1, wherein the method adopted in the step S4 is to establish the relationship between the circumferential speed, the axial speed and the circumferential speed of the turbine stage and the total parameters and the stage design parameters; the method specifically comprises the following steps:
1) Establishing a design radius R 1, high-pressure and low-pressure shaft rotating speeds N 1 and N 2, total rim work L u, work distribution coefficients omega 1～ωi of the 1 st-k-stage turbines and loading coefficients mu 1～μk of the 1 st-k-stage turbines in turbine inlet blades to calculate inlet and outlet peripheral speeds of the k-stage movable blades And/>Is a method of (2);
2) Establishing inlet and outlet peripheral speeds of the turbine inlet based on the absolute speed C 1 of the turbine inlet, the air flow angle alpha 1 of the turbine inlet and the turbine from the 1 st stage to the k th stage And/>Flow coefficient of 1 st to kth stage/>Calculating the axial velocity/>, of the inlet and outlet of the k-th stage movable bladeAnd/>Is a method of (2);
3) Establishing the turbine total rim work L u and the inlet and outlet peripheral speeds of the 1 st-kth-stage moving blades based on the absolute turbine inlet speed C 1 and the turbine inlet air flow angle alpha 1 And/>Work distribution coefficients omega 1～ωi of the 1 st-k-stage turbines calculate circumferential speeds/>, of inlet and outlet of k-stage movable bladesAnd/>Is a method of (2).
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