CN116976109A - Air film cooling modeling method considering high-temperature radiation - Google Patents
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Abstract
The invention discloses a film cooling modeling method considering high-temperature radiation, which comprises the following steps: the method comprises the steps of meeting the condition that dimensionless parameters in the traditional modeling theory are the same under different working conditions, and determining the main flow temperature and pressure under the to-be-molded working condition; the Boltzmann number and the optical thickness are increased in the traditional modeling theory; measuring the surface emissivity of the model under the to-be-molded condition, and taking the value as a known quantity; finding out a material with a heat conductivity coefficient determined by a Bi Wo number deduction formula to be used as a model material under the to-be-molded chemical condition; the size of the model air film hole under the to-be-molded working condition is determined by the main stream Reynolds number, and the size of the molded model is scaled in equal proportion; the flow rate of the main flow under the to-be-molded condition is determined by the Boltzmann number; the gas absorption coefficient of the to-be-molded working environment is determined by the optical thickness; the cold air parameters under the to-be-molded working condition are determined by the existing traditional modeling theory; the working condition parameters designed by the method can be matched with the air film cooling efficiency of the real high-temperature high-pressure engine environment.
Description
Technical Field
The invention belongs to the field of gas turbine gas film cooling design, and particularly relates to a gas film cooling modeling method considering high-temperature radiation.
Background
Film cooling is an important cooling form in a gas turbine, but due to the high-temperature working condition of the film cooling in the real gas turbine operating environment, research on film cooling performance by researchers through experimental means is restricted, mainly because it is difficult to create the same high-temperature working condition as the real gas turbine environment. However, experimental data which is nearly identical to the actual working conditions can be obtained in a laboratory more easily by modeling the theoretical design experimental working conditions.
The operating environment of real gas turbine blades is very high, exceeding 1000K, at which temperature the effect of the radiation on the turbine blade temperature must be considered. However, the importance of radiation is hardly emphasized in previous studies, and the influence of radiation is not considered in the current general modeling theory, so that the applicability of the modeling theory is challenged. In this case, film cooling efficiency obtained from a laboratory hardly reflects film cooling efficiency in a real gas turbine high temperature environment.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a film cooling modeling method considering high-temperature radiation, solves the problem that the current general modeling theory does not contain radiation influence, and provides a typical parameter matching scheme to realize the matching of the film cooling efficiency obtained in a laboratory and the efficiency of a real gas turbine environment.
In order to achieve the above object, the present invention provides the following solutions:
a film cooling modeling method considering high-temperature radiation comprises the following steps:
step one: when the dimensionless parameters in the traditional modeling theory are the same under different working conditions, determining the main flow temperature and pressure under the to-be-molded working condition; the traditional modeling theory is that when dimensionless parameters under different working conditions are guaranteed to be equal, matching of air film cooling efficiency under different working conditions is achieved; the dimensionless parameters of the existing traditional modeling theory include: main stream reynolds number, cool air reynolds number, blowing ratio, momentum ratio, speed ratio, temperature ratio, and density ratio;
step two: based on the main flow temperature and pressure, two dimensionless parameters of Boltzmann number and optical thickness are increased in the traditional modeling theory;
step three: measuring the surface emissivity of the model under the to-be-molded chemical condition;
step four: based on the surface emissivity, obtaining a material with a heat conductivity coefficient determined by a Bi Wo number deduction formula, and taking the material as a model material under the to-be-molded chemical condition;
step five: based on the main stream Reynolds number, obtaining the size of a model air film hole under the to-be-molded condition after the model material is determined, and scaling the size of the molded model;
step six: based on the Boltzmann number, obtaining the flow velocity of the main flow under the to-be-molded working condition;
step seven: based on the optical thickness, obtaining a gas absorption coefficient of the to-be-molded working environment;
step eight: based on the blowing ratio and the temperature ratio, obtaining a cool air parameter under the to-be-molded working condition;
step nine: and obtaining the air film cooling efficiency of the real high-temperature high-pressure engine environment based on the model air film hole size, the flow rate, the gas absorption coefficient and the cold air parameter after scaling in equal proportion.
Preferably, in the second step, the boltzmann number and optical thickness calculating method includes:
wherein Bo' represents Boltzmann number; ρ g Represents the main flow density; c (C) p Represents the specific heat of main flow at constant pressure; u (u) g Representing the main flow rate; epsilon represents the model emissivity; sigma represents boltzmann constant; t (T) g Representing the temperature of the main stream;
τ g ＝κ·D
wherein τ g Represents optical thickness; kappa represents the gas absorption coefficient; d represents the diameter of the air film hole.
Preferably, in the fourth step, the method for calculating the thermal conductivity coefficient includes:
wherein lambda is s1 Representing the thermal conductivity coefficient of the model under the chemical condition to be molded; lambda (lambda) s2 Representing the heat conductivity coefficient of the blade under the working condition of a real engine; k (k) g1 Representing the main flow heat conductivity coefficient under the chemical condition to be molded; k (k) g2 Representing the prevailing thermal conductivity under real engine conditions.
Preferably, in the fifth step, the method for calculating the size of the model air film hole includes:
wherein D represents the size of the air film hole; re (Re) g Representing the main flow Reynolds number; μ represents the mainstream dynamic viscosity; ρ represents the main flow density; u (u) g Representing the main flow rate.
Preferably, in the fifth step, the specific values of the scaling of the dimension of the modeling model are: and the ratio of the diameter of the air film hole of the model to be molded to the diameter of the air film hole of the blade under the working condition of the real engine.
Preferably, in the sixth step, the flow rate calculating method includes:
preferably, in the seventh step, the method for calculating the gas absorption coefficient includes:
preferably, in the eighth step, the cold air parameters include: cold air temperature and cold air flow rate;
wherein, the cold air temperature is determined by the temperature ratio:wherein T is c1 Representing the cold air temperature under the to-be-molded working condition; t (T) g2 Representing the main flow temperature under the to-be-molded condition; TR represents the temperature ratio;
the cold air flow is determined by the blowing ratio, m c1 ＝nMρ g1 u g1 A, wherein m c1 Representing the cold air flow under the to-be-molded condition; n represents the number of air film holes; m represents a blowing ratio; ρ g1 Representing the main flow density under the to-be-molded condition; u (u) g1 Representing the main flow rate under the to-be-molded condition; a represents the cross-sectional area of one air film hole.
Preferably, in the step nine, the method for calculating the adiabatic cooling efficiency of the film includes:
wherein η represents film adiabatic cooling efficiency; t (T) aw Represents an adiabatic wall temperature; t (T) c Representing the cool air temperature.
Compared with the prior art, the invention has the beneficial effects that:
the method for modeling the air film cooling by considering high-temperature radiation can solve the problem that the conventional general modeling theory does not contain radiation influence, and clearly shows how to realize the matching of the air film cooling efficiency obtained in a laboratory and the efficiency of a real gas turbine environment through a typical parameter matching scheme. The invention can provide a parameter matching method under different working conditions for the air film cooling design, solves the problem of inaccurate air film cooling efficiency mapping after radiation is considered, and has strong popularization.
Drawings
In order to more clearly illustrate the technical solutions of the present invention, the drawings that are needed in the embodiments are briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of a film cooling modeling method considering high temperature radiation in an embodiment of the invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in FIG. 1, the invention provides a film cooling modeling method considering high-temperature radiation, which establishes a set of parameter design schemes considering high-temperature and low-temperature modeling working conditions influenced by heat radiation, can solve the problem of inaccurate film cooling efficiency mapping, and is convenient for researchers to carry out experimental study on film cooling performance, and comprises the following steps:
step one: when the dimensionless parameters in the traditional modeling theory are the same under different working conditions, determining the main flow temperature and pressure under the to-be-molded working condition; the traditional modeling theory connotation means that when the fact that some dimensionless parameters under different working conditions are equal is guaranteed, the matching of the air film cooling efficiency under different working conditions can be achieved; the dimensionless parameters of the traditional modeling theory include: main stream reynolds number, cool air reynolds number, blowing ratio, momentum ratio, speed ratio, temperature ratio, and density ratio;
step two: based on the main flow temperature and pressure, two dimensionless parameters of Boltzmann number and optical thickness are added in the traditional modeling theory; wherein boltzmann number, optical thickness are used to describe radiation characteristics;
step three: measuring the surface emissivity of the model under the to-be-molded chemical condition; wherein the surface emissivity is taken as a known quantity;
step four: based on the surface emissivity, obtaining a material with a heat conductivity coefficient determined by a Bi Wo number deduction formula, and taking the material as a model material under the to-be-molded working condition;
step five: based on the main stream Reynolds number, obtaining the size of a model air film hole in the to-be-molded working condition after the model material is determined, and scaling the size of the molded model in an equal proportion;
step six: based on the boltzmann number, obtaining the flow velocity of the main flow under the to-be-molded working condition;
step seven: based on the optical thickness, obtaining a gas absorption coefficient of the to-be-molded working environment;
step eight: based on the blowing ratio and the temperature ratio, obtaining cold air parameters under the to-be-molded working condition;
step nine: and obtaining the air film cooling efficiency of the real high-temperature high-pressure engine environment based on the model air film hole size, the flow rate, the gas absorption coefficient and the cold air parameter which are scaled in equal proportion.
In the second embodiment, the boltzmann number and the optical thickness calculation method are as follows:
wherein Bo' represents Boltzmann number; ρ g Represents the main flow density; c (C) p Represents the specific heat of main flow at constant pressure; u (u) g Representing the main flow rate; epsilon represents the model emissivity; sigma represents boltzmann constant; t (T) g Representing the temperature of the main stream;
τ g ＝κ·D
wherein τ g Represents optical thickness; kappa represents the gas absorption coefficient; d represents the diameter of the air film hole.
In the fourth embodiment, the method for calculating the thermal conductivity coefficient includes:
wherein lambda is s1 Representing the thermal conductivity coefficient of the model under the chemical condition to be molded; lambda (lambda) s2 Representing the heat conductivity coefficient of the blade under the working condition of a real engine; k (k) g1 Representing the main flow heat conductivity coefficient under the chemical condition to be molded; k (k) g2 Representing the prevailing thermal conductivity under real engine conditions.
In the fifth embodiment, the method for calculating the size of the model air film hole includes:
wherein D represents the size of the air film hole; reg (Reg) Substitution of A apparent main stream reynolds number; μ represents the mainstream dynamic viscosity; ρ represents the main flow density; u (u) g Representing the main flow rate.
In the present embodiment, in the fifth step, specific values of the scaling of the dimension of the modeling model are: and the ratio of the diameter of the air film hole of the model to be molded to the diameter of the air film hole of the blade under the working condition of the real engine.
In the sixth embodiment, the flow rate calculating method includes:
in the seventh embodiment, the method for calculating the gas absorption coefficient includes:
in the present embodiment, in step eight, the cool air parameters include: cold air temperature and cold air flow rate;
wherein, the temperature of the cold air is determined by the temperature ratio:wherein T is c1 Representing the cold air temperature under the to-be-molded working condition; t (T) g2 Representing the main flow temperature under the to-be-molded condition; TR represents the temperature ratio;
the cold air flow is determined by the blowing ratio, m c1 ＝nMρ g1 u g1 A, wherein m c1 Representing the cold air flow under the to-be-molded condition; n represents the number of air film holes; m represents a blowing ratio; ρ g1 Representing the main flow density under the to-be-molded condition; u (u) g1 Representing the main flow rate under the to-be-molded condition; a represents the cross-sectional area of one air film hole.
In the embodiment, in step nine, the method for calculating the adiabatic cooling efficiency of the film is as follows:
wherein η represents film adiabatic cooling efficiency; t (T) aw Represents an adiabatic wall temperature; t (T) c Representing the cool air temperature.
Compared with the existing film cooling modeling theory, the method can consider the influence of radiation, and provides a set of low-temperature working condition parameter design scheme for considering radiation, which is more consistent with the actual working condition, and can provide an effective research tool for relevant researchers of the gas turbine.
The above embodiments are merely illustrative of the preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, but various modifications and improvements made by those skilled in the art to which the present invention pertains are made without departing from the spirit of the present invention, and all modifications and improvements fall within the scope of the present invention as defined in the appended claims.
Claims (9)
1. The film cooling modeling method considering high-temperature radiation is characterized by comprising the following steps of:
step one: when the dimensionless parameters in the traditional modeling theory are the same under different working conditions, determining the main flow temperature and pressure under the to-be-molded working condition; the traditional modeling theory is that when dimensionless parameters under different working conditions are guaranteed to be equal, matching of air film cooling efficiency under different working conditions is achieved; the dimensionless parameters of the existing traditional modeling theory include: main stream reynolds number, cool air reynolds number, blowing ratio, momentum ratio, speed ratio, temperature ratio, and density ratio;
step two: based on the main flow temperature and pressure, two dimensionless parameters of Boltzmann number and optical thickness are increased in the traditional modeling theory;
step three: measuring the surface emissivity of the model under the to-be-molded chemical condition;
step four: based on the surface emissivity, obtaining a material with a heat conductivity coefficient determined by a Bi Wo number deduction formula, and taking the material as a model material under the to-be-molded chemical condition;
step five: based on the main stream Reynolds number, obtaining the size of a model air film hole under the to-be-molded condition after the model material is determined, and scaling the size of the molded model;
step six: based on the Boltzmann number, obtaining the flow velocity of the main flow under the to-be-molded working condition;
step seven: based on the optical thickness, obtaining a gas absorption coefficient of the to-be-molded working environment;
step eight: based on the blowing ratio and the temperature ratio, obtaining a cool air parameter under the to-be-molded working condition;
step nine: and obtaining the air film cooling efficiency of the real high-temperature high-pressure engine environment based on the model air film hole size, the flow rate, the gas absorption coefficient and the cold air parameter after scaling in equal proportion.
2. The method for modeling a film cooling system in consideration of high-temperature radiation as defined in claim 1, wherein in the second step, the boltzmann number and optical thickness calculation method is as follows:
wherein Bo' represents Boltzmann number; ρ g Represents the main flow density; c (C) p Represents the specific heat of main flow at constant pressure; u (u) g Representing the main flow rate; epsilon represents the model emissivity; sigma represents boltzmann constant; t (T) g Representing the temperature of the main stream;
τ g ＝κ·D
wherein τ g Represents optical thickness; kappa represents the gas absorption coefficient; d represents the diameter of the air film hole.
3. The method for modeling film cooling taking high-temperature radiation into consideration as defined in claim 1, wherein in the fourth step, the method for calculating the thermal conductivity is as follows:
wherein lambda is s1 Representing the thermal conductivity coefficient of the model under the chemical condition to be molded; lambda (lambda) s2 Representing the heat conductivity coefficient of the blade under the working condition of a real engine; k (k) g1 Representing the main flow heat conductivity coefficient under the chemical condition to be molded; k (k) g2 Representing the prevailing thermal conductivity under real engine conditions.
4. The method for modeling gas film cooling taking high-temperature radiation into consideration as defined in claim 1, wherein in the fifth step, the method for calculating the size of the model gas film hole is as follows:
wherein D represents the size of the air film hole; re (Re) g Representing the main flow Reynolds number; μ represents the mainstream dynamic viscosity; ρ represents the main flow density; u (u) g Representing the main flow rate.
5. The method of modeling film cooling taking into account high temperature radiation as defined in claim 1, wherein in the fifth step, the specific values of the scaling of the modeling model are: and the ratio of the diameter of the air film hole of the model to be molded to the diameter of the air film hole of the blade under the working condition of the real engine.
6. The method for modeling film cooling taking into account high temperature radiation as defined in claim 1, wherein in the step six, the flow rate calculating method is as follows:
7. the method for modeling film cooling taking high-temperature radiation into consideration as defined in claim 1, wherein in the seventh step, the method for calculating the gas absorption coefficient is as follows:
8. the method of film cooling modeling in view of high temperature radiation as defined in claim 1, wherein in the eighth step, the cool air parameters include: cold air temperature and cold air flow rate;
wherein the cool air temperatureIs determined by the temperature ratio:wherein T is c1 Representing the cold air temperature under the to-be-molded working condition; t (T) g2 Representing the main flow temperature under the to-be-molded condition; TR represents the temperature ratio;
the cold air flow is determined by the blowing ratio, m c1 ＝nMρ g1 u g1 A, wherein m c1 Representing the cold air flow under the to-be-molded condition; n represents the number of air film holes; m represents a blowing ratio; ρ g1 Representing the main flow density under the to-be-molded condition; u (u) g1 Representing the main flow rate under the to-be-molded condition; a represents the cross-sectional area of one air film hole.
9. The method for modeling film cooling taking into account high temperature radiation as defined in claim 1, wherein in step nine, the method for calculating the film adiabatic cooling efficiency is as follows:
wherein η represents film adiabatic cooling efficiency; t (T) aw Represents an adiabatic wall temperature; t (T) c Representing the cool air temperature.
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