CN116432342A - Air supply and collection cavity of anti-icing system and optimization method thereof - Google Patents

Air supply and collection cavity of anti-icing system and optimization method thereof Download PDF

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Publication number
CN116432342A
CN116432342A CN202310352992.3A CN202310352992A CN116432342A CN 116432342 A CN116432342 A CN 116432342A CN 202310352992 A CN202310352992 A CN 202310352992A CN 116432342 A CN116432342 A CN 116432342A
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air supply
collection cavity
collection
aspect ratio
heat transfer
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李淼
刘国朝
龚欢
李云单
张程东
贾琦
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AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • 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
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • 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
    • G06F2113/00—Details relating to the application field
    • G06F2113/14—Pipes
    • 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
    • G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
    • 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
    • G06F2119/06—Power analysis or power optimisation
    • 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
    • G06F2119/08—Thermal analysis or thermal optimisation
    • 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

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Abstract

The application provides an optimization method of an air supply and collection cavity of an anti-icing system, which comprises the following steps: constructing characteristic parameters of the air supply and collection cavity, wherein the characteristic parameters are the aspect ratio of the air supply and collection cavity; taking a plurality of values between the minimum value and the maximum value of the aspect ratio according to a preset interval to form N aspect ratios comprising the minimum value and the maximum value of the aspect ratio, and carrying out three-dimensional network modeling on the flow heat transfer characteristics of the air supply and collection cavity based on the N aspect ratios to form N calculation models altogether; the method comprises the steps of carrying out weight evaluation and hydrodynamic force calculation of air supply and collection cavities based on N calculation models to obtain weight evaluation results and flow heat transfer characteristics of the N air supply and collection cavities, and respectively establishing weight evaluation result curves and flow heat transfer characteristic curves of the N air supply and collection cavities by taking N aspect ratios as abscissa; and placing the weight evaluation result curve and the flow heat transfer characteristic curve under the same aspect ratio coordinate system, wherein the aspect ratio corresponding to the intersection point of the weight evaluation result curve and the flow heat transfer characteristic curve is the optimal structure of the air supply and collection cavity.

Description

Air supply and collection cavity of anti-icing system and optimization method thereof
Technical Field
The application belongs to the technical field of gas turbine engines, and particularly relates to an air supply and collection cavity of an anti-icing system and an optimization method thereof.
Background
When an aircraft flies in an icing envelope, the supercooled water drops can freeze the surfaces of engine inlet components (fairing, caps, etc.) due to the supercooled water drops in the air. Icing of the engine inlet component can change its aerodynamic profile, reducing the intake area of the airflow at the inlet, resulting in reduced aerodynamic performance. Meanwhile, the ice deposition falls off, and parts such as engine blades and the like can be damaged, so that mechanical damage is caused, and therefore, the engine inlet part needs to be protected from ice.
In a common anti-icing system, a hot gas is led from the tip of a stator blade of a certain-level high-pressure compressor, and is conveyed to a gas supply and collection cavity through a pipeline, and the gas supply and collection cavity distributes and conveys the hot gas into an inlet anti-icing component, so that anti-icing protection is provided for the inlet anti-icing component, and safe and stable operation of an engine in a flight envelope is ensured.
The hot gas enters the air supply and collection cavity from the air inlet and moves along the circumferential direction of the air supply and collection cavity, and heat exchange exists between the hot gas and air flow in the main channel of the engine in the movement process. Because the air supply and collection cavity is made of metal materials generally, and the metal materials have large heat conductivity coefficients, the heat exchange between hot air and a main runner is severe, the temperature of the hot air is reduced greatly, the temperature of the hot air entering the furthest anti-icing component is insufficient, and the anti-icing component cannot perform anti-icing well. In order to ensure the anti-icing effect of the furthest anti-icing component, a mode of improving the anti-icing gas consumption is generally adopted, but because the anti-icing hot gas is high-temperature and high-pressure air led from the high-pressure air compressor, the engine is surge due to excessive increase of the anti-icing gas consumption, and the engine is threatened to work.
Disclosure of Invention
The invention aims to provide an air supply and collection cavity of an anti-icing system and an optimization method thereof, which are used for solving or alleviating at least one problem in the background technology.
The technical scheme of the application is as follows: an optimization method of an air supply and collection cavity of an anti-icing system comprises the following steps:
constructing characteristic parameters of the air supply and collection cavity, wherein the characteristic parameters are the aspect ratio of the air supply and collection cavity;
taking a plurality of values between the minimum value and the maximum value of the aspect ratio according to a preset interval to form N aspect ratios comprising the minimum value and the maximum value of the aspect ratio, and carrying out air supply and collection cavity flow heat transfer characteristic calculation three-dimensional network modeling based on the N aspect ratios to form N calculation models corresponding to the N aspect ratios;
carrying out weight evaluation and hydrodynamic force calculation of the air supply and collection cavities based on the N calculation models to obtain weight evaluation results and flow heat transfer characteristics of the N air supply and collection cavities, and respectively establishing weight evaluation result curves and flow heat transfer characteristic curves of the N air supply and collection cavities by taking the N aspect ratios as abscissa coordinates;
and placing the weight evaluation result curve and the flow heat transfer characteristic curve of the air supply and collection cavity under the same aspect ratio coordinate system, wherein the aspect ratio corresponding to the intersection point of the weight evaluation result curve and the flow heat transfer characteristic curve is the optimal structure of the air supply and collection cavity.
Further, when the aspect ratio is taken, the aspect ratio is satisfied that the flow area of the hot gas inside the gas supply and collection cavity is unchanged.
Further, the flow heat transfer characteristic comprises a hot gas temperature drop.
In addition, the application also provides an air supply and collection cavity of the anti-icing system, and the air supply and collection cavity is designed by adopting the air supply and collection cavity optimization method of the anti-icing system.
Further, a partition plate is arranged in the hot gas channel inside the gas supply and collection cavity, and the partition plate enables the part, close to the inner side, inside the gas supply and collection cavity to form an air interlayer.
Further, the thickness of the air interlayer is 0.8 mm-2 mm.
Further, a heat-insulating coating is sprayed on the inner ring surface outside the air supply and collection cavity.
Further, the thickness of the thermal insulation coating is 0.3 mm-0.8 mm.
According to the air supply and collection cavity of the anti-icing system and the optimization method thereof, the problem that the temperature of hot air of an existing air supply and collection cavity structure is reduced along the process can be solved, the anti-icing air-entraining amount is reduced on the premise that the most severe anti-icing component meets the anti-icing requirement, the energy consumption of an engine is reduced to the greatest extent, and the safe and stable operation of the engine is ensured.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a front view of a typical anti-icing system.
FIG. 2 is a side view of a typical anti-icing system.
FIG. 3 is a schematic view of a gas supply and collection chamber.
FIG. 4 is a schematic view of the direction of flow of hot gas and the wide and high positions of the gas collection chamber.
Fig. 5 is a schematic diagram of the method of the present application.
Fig. 6 is a schematic representation of weight versus aspect ratio in the present application.
FIG. 7 is a graphical representation of hot gas temperature drop versus aspect ratio for the present application.
FIG. 8 is a graph illustrating weight versus aspect ratio in an embodiment of the present application.
FIG. 9 is a graph illustrating hot gas temperature drop versus aspect ratio in an embodiment of the present application.
FIG. 10 is a graphical representation of hot gas temperature drop versus aspect ratio for the present application.
FIG. 11 is a graph illustrating hot gas temperature drop versus aspect ratio in an embodiment of the present application.
FIG. 12 is a schematic view of the final air supply and collection cavity structure in an embodiment of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
As shown in fig. 1 to 4, a typical aircraft engine anti-icing system is schematically shown, which comprises a bleed air seat 1, an air supply and collection cavity 2 and anti-icing components consisting of a rectifying support plate 3 and a cap 4, wherein the rectifying support plate 3 and the cap 4 are components which need to provide anti-icing protection. The anti-icing system leads out high-temperature and high-pressure air from the blade tips of a certain stage of stator blade of the high-pressure compressor, the high-temperature and high-pressure air enters the air supply and collection cavity 2 through the air-entraining seat 1, hot air flows along the circumferential direction of the air supply and collection cavity 2, and continuously flows from the air outlet 5 to the rectifying support plate 3 in the flowing process. After the hot air entering the rectifying support plate 3 heats and prevents ice on the wall surface, one part of hot air flows into the main runner, and the other part flows into the cap cover 4, so that the wall surface of the cap cover 4 is continuously protected from ice.
In order to reduce the temperature drop of hot air in the air supply and collection cavity to the greatest extent, the structural weight of the air supply and collection cavity is reduced while the anti-icing requirement of an engine is effectively met, and the influence of anti-icing air entraining on the performance and safety of the engine is reduced, the application provides an optimization method of the air supply and collection cavity of the anti-icing system with high efficiency and low heat loss.
As shown in fig. 5, the method for optimizing the air supply and collection cavity of the anti-icing system provided by the application comprises the following steps:
firstly, constructing characteristic parameters of the air supply and collection cavity, wherein the characteristic parameters are the aspect ratio of the air supply and collection cavity, namely K=L/H, L is the axial length of the air supply and collection cavity, and H is the radial height of the air supply and collection cavity.
As can be seen from the installation position of the air supply and collection cavity 2 in the engine and the actual working state thereof, most of the heat exchange between the air supply and collection cavity 2 and the outside is concentrated in the inner ring direction between the inner anti-icing hot air flow and the main channel air flow of the engine, as shown in fig. 4, which is a main structural factor affecting the temperature drop of the air supply and collection cavity. In order to ensure that the anti-icing gas consumption can meet the requirement, the internal flow area needs to be kept unchanged, and based on this, it is proposed in the application to construct a characteristic parameter, wherein the characteristic parameter is the aspect ratio of the gas supply and collection cavity, i.e. k=l/H, L is the axial length, and H is the height.
Taking a plurality of values between the minimum value and the maximum value of the aspect ratio at a certain interval to form N aspect ratios comprising the minimum value and the maximum value, and carrying out three-dimensional network modeling on the flow heat transfer characteristics of the air supply and collection cavity based on the N different aspect ratios to form N calculation models corresponding to the number N of the aspect ratios.
Assuming that the aspect ratios K are several values at intervals from the aspect ratio k=0 to a certain theoretical maximum k×max (e.g. the air supply structure has no height, like a plane), N aspect ratio values k×min, k×1, k×2 … … k×max are formed, the aspect ratio is selected on the basis of ensuring that the internal hot air flow area is unchanged, i.e. lxh=const.
And according to the determined N different aspect ratios K, carrying out flow heat transfer characteristic calculation three-dimensional network modeling of the air supply and collection cavity 2, and forming N calculation models corresponding to the N number of the aspect ratios K.
For example, in one embodiment of the present application, for the optimization requirements of an air and gas collection cavity 2 of an anti-icing system of a certain type of engine, a series of 15 structures are assumed that the air and gas collection cavity aspect ratios k=0.8, 0.17, 0.31, 0.48, 0.68, 0.94, 1.23, 1.55, 1.92, 2.32, 2.76, 3.24, 3.79, 4.31, 4.91 can be implemented by the engine. And carrying out three-dimensional network modeling on flow heat transfer characteristics calculation of the air supply and collection cavity 2, and forming 15 calculation models corresponding to the number K of the aspect ratio.
And thirdly, carrying out weight evaluation and hydrodynamic force calculation on the N calculation models to obtain weight evaluation results and flow heat transfer characteristics of N air supply and collection cavities corresponding to the N calculation models, and respectively establishing weight evaluation result curves and flow heat transfer characteristic curves of the N air supply and collection cavities by taking the N aspect ratios as abscissa.
And adopting three-dimensional simulation calculation to respectively carry out hydrodynamic calculation solution on the N calculation models, and calculating to obtain a series of flow heat transfer characteristics of the air supply and collection cavity, wherein the flow heat transfer characteristics comprise hot air temperature drop.
Meanwhile, for N calculation models, the weight evaluation results of the air supply and collection cavities corresponding to the N calculation models can be obtained in the three-dimensional modeling software.
As shown in fig. 6, the weight-to-width ratio variation curve of the air supply and collection chamber is plotted with the weight evaluation results of the N calculation models as the ordinate on the abscissa of the N aspect ratios. Typically, the weight of the air supply and collection chamber is represented by the aspect ratio curve: as the aspect ratio increases, the weight of the gas supply and collection chamber 2 decreases.
As shown in fig. 7, the hot gas temperature drop of the gas supply and collection chamber 2 is plotted as a function of the aspect ratio, with the N aspect ratios being on the abscissa and the flow heat transfer characteristic characterized by the hot gas temperature drop being on the ordinate. In general, the hot gas temperature drop of the gas supply and collection cavity is expressed in terms of an aspect ratio curve: as the aspect ratio increases, the hot gas temperature drop increases gradually.
The weight-to-aspect ratio change curve of the air supply and collection cavity and the hot air temperature drop of the air supply and collection cavity corresponding to the 15 calculation models in the above embodiment of the application are shown in fig. 8 and 9.
And fourthly, placing the weight evaluation result curve and the flow heat transfer characteristic curve under the same coordinate system, wherein the aspect ratio corresponding to the intersection point of the two curves is the optimal structure of the air supply and collection cavity.
As shown in fig. 10, fig. 6 and fig. 7 are drawn in the same aspect ratio coordinate system, a curve intersection point exists between the weight of the air supply and collection cavity along with the aspect ratio change curve and the hot air temperature drop of the air supply and collection cavity along with the aspect ratio change curve, and the aspect ratio corresponding to the curve intersection point is the optimal solution of the air supply and collection cavity 2 by comprehensively considering the weight and the hot air temperature drop.
As shown in fig. 11, in the embodiment of the 15 calculation models described above in the present application, fig. 8 and 9 are plotted under the same aspect ratio coordinate system, where the intersection point of the two curves is at the aspect ratio of 0.48, so that the aspect ratio of 0.48 is the optimal solution of the air supply and collection cavity.
In addition, the application also provides a gas supply and collection cavity for the anti-icing system, and the gas supply and collection cavity is designed by adopting the optimization method of the gas supply and collection cavity of the anti-icing system.
In this application, be equipped with baffle 21 in the inside steam passageway of air feed gas collection chamber, the baffle 21 makes the inside cavity part that is close to the inboard of air feed gas collection chamber form the air intermediate layer, and this air intermediate layer can further reduce the steam temperature drop of air feed gas collection chamber. In addition, a heat-insulating coating 22 is sprayed on the inner annular surface of the outer part of the air supply and collection cavity, so that the heat resistance of hot air and a main runner is increased, and the heat exchange strength is weakened.
In the preferred embodiment of the present application, considering the actual installation of the air supply and collection chamber on the engine, the thickness of the air interlayer and the thermal insulation coating depends on the height of the air supply and collection chamber, and the thickness of the air interlayer can be generally set to be (0.8-2) mm, and the thickness of the thermal insulation coating can be set to be (0.3-0.8) mm;
the air supply and collection chamber for the anti-icing system provided in the present application may be any substrate, not limited to metallic materials and composite materials.
According to the air supply and collection cavity of the anti-icing system and the optimization method thereof, the problem that the temperature of hot air of an existing air supply and collection cavity structure is reduced along the process can be solved, the anti-icing air-entraining amount is reduced on the premise that the most severe anti-icing component meets the anti-icing requirement, the energy consumption of an engine is reduced to the greatest extent, and the safe and stable operation of the engine is ensured.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (8)

1. An optimization method of an air supply and collection cavity of an anti-icing system is characterized by comprising the following steps:
constructing characteristic parameters of the air supply and collection cavity, wherein the characteristic parameters are the aspect ratio of the air supply and collection cavity;
taking a plurality of values between the minimum value and the maximum value of the aspect ratio according to a preset interval to form N aspect ratios comprising the minimum value and the maximum value of the aspect ratio, and carrying out air supply and collection cavity flow heat transfer characteristic calculation three-dimensional network modeling based on the N aspect ratios to form N calculation models corresponding to the N aspect ratios;
carrying out weight evaluation and hydrodynamic force calculation of the air supply and collection cavities based on the N calculation models to obtain weight evaluation results and flow heat transfer characteristics of the N air supply and collection cavities, and respectively establishing weight evaluation result curves and flow heat transfer characteristic curves of the N air supply and collection cavities by taking the N aspect ratios as abscissa coordinates;
and placing the weight evaluation result curve and the flow heat transfer characteristic curve of the air supply and collection cavity under the same aspect ratio coordinate system, wherein the aspect ratio corresponding to the intersection point of the weight evaluation result curve and the flow heat transfer characteristic curve is the optimal structure of the air supply and collection cavity.
2. The method for optimizing an air supply and collection cavity of an anti-icing system according to claim 1, wherein the aspect ratio is such that the hot air flow area within the air supply and collection cavity is unchanged.
3. The method of optimizing an air supply and collection cavity of an anti-icing system of claim 1 wherein said flow heat transfer characteristics comprise a hot gas temperature drop.
4. An air supply and collection cavity of an anti-icing system, which is characterized in that the air supply and collection cavity is designed by adopting the optimization method of the air supply and collection cavity of the anti-icing system according to any one of claims 1 to 3.
5. The anti-icing system air supply and collection cavity of claim 4 wherein a baffle is positioned in the hot gas path within said air supply and collection cavity, said baffle providing an air interlayer within the interior of said air supply and collection cavity adjacent the interior.
6. The anti-icing system air supply and air collection cavity of claim 5 wherein said air interlayer has a thickness of 0.8mm to 2mm.
7. An air supply and collection chamber of an anti-icing system as recited in any one of claims 4 to 6, wherein a thermal barrier coating is sprayed on the inner annulus outside of said air supply and collection chamber.
8. The anti-icing system air supply and air collection chamber of claim 7 wherein said thermal barrier coating has a thickness of 0.3mm to 0.8mm.
CN202310352992.3A 2023-04-04 2023-04-04 Air supply and collection cavity of anti-icing system and optimization method thereof Pending CN116432342A (en)

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CN202310352992.3A CN116432342A (en) 2023-04-04 2023-04-04 Air supply and collection cavity of anti-icing system and optimization method thereof

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