Oil-gas matching intelligent adjusting technology self-adaptive to inlet distortion

Abstract

The invention discloses an oil-gas matching intelligent adjusting technology self-adaptive to inlet distortion, and the core idea is that under the condition of a distorted inlet, a plurality of temperature and pressure measuring points are arranged at the front edge of a support plate, the pressure and temperature parameters of incoming flow can be obtained, and inlet static pressure is combined, so that the inlet distortion is adjusted. The measured data are input into an algorithm program to obtain the radial speed and temperature change trend of the airflow, then the airflow flow of each stage is calculated according to the radial classification of the nozzle at the tail edge of the supporting plate, and the fuel oil flow of each stage is obtained according to oil-gas matching, namely that the oil-gas ratio of each stage is kept consistent with the total oil-gas ratio; and then the mass flow controller controls the nozzle to perform fuel injection. And fuel oil supply can be flexibly adjusted according to actual requirements through radial graded oil supply of the supporting plate, so that the fuel oil concentration distribution behind the supporting plate is more uniform, and the combustion efficiency and the combustion stability of the afterburner are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of afterburner of gas turbines, specifically an intelligent regulation technology for oil-gas matching with adaptive inlet distortion, which can achieve oil-gas matching under inlet distortion and significantly improve the combustion efficiency and combustion stability of the afterburner. Background Art

[0002] The rectifying and supporting device of the traditional turbine component in the new generation of afterburner is moved backward into the afterburner for integrated design, so the inlet section of the integrated afterburner is moved forward to the outlet section of the turbine rotor blade. The wake effect generated by the rotation of the turbine blade, the instability of the turbine operation, the cooling of the turbine wall by the cooling air, and the discontinuous fuel injection of the main combustor result in non-uniform distribution of the turbine outlet velocity and temperature, making the inlet condition of the afterburner worse, leading to the non-uniformity of the inlet velocity and temperature of the integrated afterburner, which is one of the important factors affecting the stable operation of the afterburner.

[0003] At the same time, the new generation of wide-range variable cycle engine realizes the thrust requirements of subsonic cruise and supersonic cruise in the speed range of 0 - 5Ma through the characteristics of multi-duct variable function switching and multi-component variable cycle combination. During the change process of each duct and cycle, the bypass ratio will change greatly from a low bypass ratio to a medium-high bypass ratio. At the same time, the main combustor and the dual variable combustor will be in a single or combined multi-state combustion mode, which will lead to a drastic non-uniform distribution characteristic of the inlet velocity and temperature of the afterburner, and the peak position changes radially with the working condition.

[0004] The parameters of the inner and outer ducts of the wide-range variable cycle afterburner change within a large range, and the large distortion of the inlet velocity and temperature increases the difficulty of organizing combustion in the afterburner. When the incoming flow temperature distortion is relatively high, the influence is particularly significant, and it is easy to form local rich oil areas or local thermal blockage areas, resulting in a decrease in combustion efficiency and combustion stability. The traditional fixed fuel supply method will cause a drastic non-uniformity in the spatial distribution of the oil-gas ratio under large inlet velocity distortion; while the inlet temperature distortion will cause rapid evaporation in some areas, leading to spontaneous combustion and ablation. Summary of the Invention

[0005] In view of the above-mentioned existing technical defects, the present invention is based on an intelligent adjustment technology for oil-gas matching with adaptive inlet distortion, which can effectively improve the uniformity of the fuel concentration distribution behind the strut, and improve the combustion efficiency and combustion stability. The present invention discloses an intelligent adjustment technology for oil-gas matching with adaptive inlet distortion, aiming to meet the oil-gas matching by adopting a radial grading fuel supply mode for the strut under the oncoming flow conditions of inlet distortion, and accurately control the position and flow rate of fuel supply under the distorted oncoming flow conditions. By arranging a plurality of pressure and temperature measuring points at the leading edge of the strut, the pressure and temperature parameters of the oncoming flow can be obtained simultaneously. Combining with the algorithm program, the fuel flow rate of each nozzle at the trailing edge of the strut can be obtained according to the data measured at the leading edge of the strut. The nozzle is connected to the mass flow controller, and the fuel flow rate data of each stage is input into the mass flow controller, which automatically controls the nozzle to inject fuel, finally realizing the radial grading fuel supply of the strut, making the fuel concentration distribution behind the strut more uniform, and improving the combustion efficiency and combustion stability of the afterburner.

[0006] The present invention is implemented as follows:

[0007] An intelligent adjustment technology for oil-gas matching with adaptive inlet distortion includes the following:

[0008] Under the inlet conditions of distorted oncoming flow, by arranging a plurality of temperature and pressure measuring points at the leading edge of the strut, the pressure and temperature parameters of the oncoming flow are measured. Combining with the inlet static pressure, the measured data is input into the algorithm program to obtain the velocity distribution trend of the air flow along the radial direction; according to the radial grading of the nozzles at the trailing edge of the strut, the air flow rate of each stage is calculated, and the fuel flow rate of each stage is obtained based on the oil-gas matching, that is, the oil-gas ratio of each stage is kept consistent with the total oil-gas ratio; a plurality of stages of fuel nozzles are arranged in a staggered manner at the trailing edge of the strut. After the nozzles pass through the fuel supply pipeline, they are connected to the mass flow controller. The required fuel flow rate of each stage is input into the mass flow controller to control the fuel injection, realizing the oil-gas matching under the intake distortion, making the fuel concentration distribution behind the strut more uniform, and improving the combustion efficiency and combustion stability of the afterburner.

[0009] Further, the length direction of the strut is consistent with the oncoming flow direction, and the upstream end in the length direction of the strut forms its leading edge end face, and the downstream end forms the trailing edge end face of the strut.

[0010] Further, a plurality of temperature and pressure measuring points are uniformly arranged along the radial direction of the strut, and the pressure and temperature parameters of the oncoming flow can be measured simultaneously. Among them, the thermocouple wire is fixed in the temperature / pressure measurement channel, and the extended part length is used to measure the oncoming flow temperature, and the other end is connected to the temperature measuring device through the compensating wire; after the total pressure measuring point measures the total pressure of the oncoming flow, the total pressure tube is connected to the pressure measuring device.

[0011] Furthermore, four - stage fuel nozzles are stagger - arranged at the trailing edge of the strut. The nozzles are evenly distributed along the height direction of the strut, divided into four regions, with each region containing four nozzles, forming a radial grading. The nozzles are connected to the fuel supply pipeline, and the other end of the nozzle is connected to a mass flow controller, and the fuel injection of the nozzle is automatically adjusted by the mass flow controller. There is a four - stage fuel injection structure stagger - arranged at the trailing edge of the strut of the present invention. Each stage includes four nozzles. The fuel nozzles are evenly distributed along the height direction of the strut. The nozzles are connected to the fuel supply pipeline. The radial grading method is adopted to adjust the fuel supply mode. The other end of the nozzle is connected to a mass flow controller. The fuel flow of each stage is input into the mass flow controller, and the fuel injection of the nozzle is automatically controlled by the mass flow controller, realizing a more uniform fuel concentration distribution, meeting the requirements for fuel distribution under different distortion conditions, solving the problem of uneven oil - gas matching of the strut in the afterburner under distorted flow, and improving the combustion efficiency and combustion stability.

[0012] Furthermore, the nozzles of each stage are stagger - arranged, and the fuel supply pipeline is located between two nozzles on the same side, ensuring that the fuel injection amounts of the two nozzles are the same. The mass flow controller of each stage can independently adjust the fuel flow. The mass flow controller has a fast response ability, can quickly complete the adjustment, and has high precision and high reliability.

[0013] Furthermore, the overall strut is symmetric on the left and right sides in its width direction. The nozzles at the trailing edge of the strut are stagger - arranged, which can be divided into multiple regions, forming a radial grading. The spacing between the nozzles and the number of radial gradings are not restricted and can be graded according to actual needs.

[0014] 1. In the wide - range variable - cycle afterburner, the parameter variation ranges of the inner and outer flows are large, and the large distortion of the inlet velocity and temperature increases the difficulty of organizing combustion in the afterburner. For the intelligent regulation technology of oil - gas matching with adaptive inlet distortion of the present invention, under the inlet condition of distorted flow, by arranging multiple temperature and pressure measurement points at the leading edge of the strut, the pressure and temperature parameters of the incoming flow are measured. The measured data are input into the algorithm program to obtain the velocity and temperature distribution trends of the air flow along the radial direction as shown in Equation (1). Then, according to the radial grading of the nozzles at the trailing edge of the strut, the air flow rate of each stage is calculated as shown in Equation (2), and based on the oil - gas matching, that is, the oil - gas ratio of each stage is kept consistent with the total oil - gas ratio, the fuel flow rate of each stage is obtained as shown in Equation (3).

[0015] v = f(p, p0, T) (1)

[0016] m i,air = f(v, ρ, A) (2)

[0017] m i,f = α * m i,air = f(α, v, ρ, A) (3)

[0018] Among them, p is the static pressure of the incoming flow, p0 is the total pressure at the leading edge of the strut, T is the total temperature at the leading edge of the strut, v is the radial velocity of the strut, A is the cross-sectional area of the incoming flow, ρ is the air density, m i,air is the air flow rate of each stage, and m i,f is the fuel flow rate of each stage, and α is the fuel-air ratio.

[0019] The technical core of the present invention is the intelligent adjustment technology of fuel-air matching for adaptive inlet distortion. Under the distorted incoming flow inlet conditions, multiple temperature and pressure measurement points are arranged at the leading edge of the strut to measure the pressure and temperature parameters of the incoming flow. Combining with the inlet static pressure, the obtained data is input into the calculation program to obtain the radial velocity and temperature radial distribution of the air flow. Then, according to the radial grading of the nozzles at the trailing edge of the strut, the air flow rate of each stage is calculated, and the fuel flow rate of each stage is obtained based on the fuel-air matching, that is, the fuel-air ratio of each stage is kept consistent with the total fuel-air ratio. There are multiple stages of fuel injection structures arranged in a staggered manner at the trailing edge of the strut, and the fuel supply adopts the radial grading fuel supply method. According to the distribution law of the velocity and temperature along the radial direction measured in front of the strut and the fuel-air ratio, the fuel flow rate required for each stage of fuel supply is calculated to meet the uniform distribution of the fuel-air ratio behind the flame holder; the fuel nozzle is connected to the mass flow controller, and the fuel flow rate of each stage is input into the mass flow controller to automatically control the fuel injection of the nozzle, achieving the purpose of radially grading the fuel distribution, flexibly adjusting the fuel supply amount in different regions according to the actual incoming flow distortion conditions, making the fuel concentration distribution more uniform, ensuring reliable ignition, flame linking and stable combustion of the combustion chamber, and improving the performance of the afterburner.

[0020] The beneficial effects of the present invention compared with the prior art are as follows:

[0021] 1) The intelligent adjustment technology of fuel-air matching for adaptive inlet distortion of the present invention is applied to the afterburner under distorted incoming flow. Multiple measurement points arranged at the leading edge of the strut can simultaneously measure the temperature and pressure parameters of the incoming flow. After calculation by the algorithm program, the distribution trends of the velocity and temperature in the radial direction of the strut are obtained. According to the radial grading of the nozzles at the trailing edge of the strut, the fuel flow rate required for each stage can be calculated, which can more accurately control the fuel supply, ensure the best fuel-air mixing ratio, and improve the combustion efficiency.

[0022] 2) The intelligent adjustment technology of fuel-air matching for adaptive inlet distortion of the present invention can meet the fuel flow rate requirements under different distorted incoming flow conditions. The radial grading fuel supply method at the trailing edge of the strut can automatically adjust the fuel flow rate through the mass flow controller, can flexibly adjust the fuel supply strategy according to different inlet conditions, and adapt to the requirements of various working conditions, with high flexibility.

[0023] 3) The traditional fixed fuel supply method is difficult to adapt to complex distorted flow environments, resulting in problems such as incomplete combustion and unstable flames. The intelligent adjustment technology for oil-gas matching with adaptive inlet distortion of the present invention can hierarchically control the fuel flow of each stage of the nozzle at the trailing edge of the strut according to the airflow parameters at the leading edge of the strut through an algorithm program, making the fuel concentration distribution more uniform behind the strut, and significantly improving the combustion efficiency and combustion stability of the afterburner. Description of the Drawings

[0024] Figure 1 is the left view of the intelligent adjustment technology device for oil-gas matching with adaptive inlet distortion;

[0025] Figure 2 is the sectional view of the intelligent adjustment technology device for oil-gas matching with adaptive inlet distortion;

[0026] Figure 3 is the front view of the intelligent adjustment technology device for oil-gas matching with adaptive inlet distortion;

[0027] Figure 4 is the schematic diagram of pressure / temperature measurement of the intelligent adjustment technology device for oil-gas matching with adaptive inlet distortion;

[0028] Figure 5 is the schematic diagram of the intelligent control system for oil-gas matching with adaptive inlet distortion.

[0029] Among them, 1 - strut, 2 - nozzle, 3 - fuel supply pipeline, 4 - total pressure / total temperature measurement channel, 5 - temperature compensation wire, 6 - total pressure pipe, 7 - thermocouple wire, 8 - total pressure measurement point. Detailed Embodiment

[0030] To make the purpose and effects of the present invention clearer and more definite, the present invention is further described in detail below with reference to the accompanying drawings. It should be noted that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention.

[0031] As Figures 1 to 4 shown, it is the intelligent adjustment technology device for oil-gas matching with adaptive inlet distortion of the present invention, mainly including structural components such as a strut 1, a nozzle 2, a temperature / pressure measurement structure, and a fuel supply pipeline 3. Among them, the length direction of the strut is basically consistent with the oncoming flow direction, and the upstream end in its length direction forms its leading edge end face, and the downstream end forms its trailing edge end face. A plurality of temperature and pressure measurement points are arranged at the leading edge of the strut, evenly distributed along the radial direction of the strut, and can simultaneously measure the total pressure and temperature of the oncoming flow. The measurement component and the measurement channel are filled with high-temperature resistant materials for sealing to ensure that the airflow does not leak, and at the same time ensure that the air around the measurement device is stagnant to ensure the accuracy of the pressure and temperature measurement data.

[0032] As Figure 2As shown, the fuel injection structure includes a fuel supply passage 3 and fuel nozzles 2 evenly distributed in a staggered manner. The nozzles adopt radial staging, which is divided into four levels. Figure 2 In the four regions shown, there are four nozzles in each level, two on each of the left and right sides. The nozzles on the same side of each level are connected to a fuel passage, and the other end is connected to a mass flow controller. The controller independently controls the fuel flow of each level of nozzles. The spacing between the nozzles and the number of radial staging levels are not restricted and can be staged according to actual needs.

[0033] As Figure 3 shown, the splitter plate is symmetrically distributed on the left and right sides in its width direction, so that the channel geometric structures on both sides of the splitter plate are the same, ensuring the same flow field environment on both sides and the same fuel flow on both sides of each level.

[0034] As Figure 4 shown, the measuring points at the leading edge of the splitter plate can simultaneously measure the pressure and temperature of the oncoming flow. Among them, the thermocouple wire 7 is fixed in the temperature / pressure measurement channel 4, and the protruding part length is used to measure the oncoming flow temperature. The other end is connected to the temperature measurement device through the compensating wire 5. After the total pressure measuring point 8 measures the total pressure of the oncoming flow, the total pressure tube 6 is connected to the pressure measurement device to obtain the pressure and temperature parameters of the air flow. Combining with the inlet static pressure, through algorithmic programs, the velocity and temperature distribution trends in the radial direction of the splitter plate are obtained as shown in Equation (1), and then according to Figure 2 the number of radial staging levels of the nozzles at the trailing edge of the splitter plate, the air flow rate of each level is calculated as shown in Equation (2), and based on the fuel-air matching, that is, the fuel-air ratio of each level is kept consistent with the total fuel-air ratio, the fuel flow rate of each level is obtained as shown in Equation (3).

[0035] v = f(p, p0, T) (1)

[0036] m i,air = f(v, ρ, A) (2)

[0037] m i,f = α * m i,air = f(α, v, ρ, A) (3)

[0038] where p is the oncoming flow static pressure, p0 is the total pressure at the leading edge of the splitter plate, T is the total temperature at the leading edge of the splitter plate, v is the radial velocity of the splitter plate, A is the oncoming flow cross-sectional area, ρ is the air flow density, m i,air is the air flow rate of each level, m i,f is the fuel flow rate of each level, and α is the fuel-air ratio. After obtaining the fuel flow rate of each level, set the mass flow controller to automatically control the fuel injection of each level of nozzles.

[0039] The working process of the present invention:

[0040] The intelligent adjustment technology for oil-gas matching with adaptive inlet distortion of the present invention can obtain the pressure and temperature parameters of the incoming flow by arranging multiple pressure and temperature measurement points at the leading edge of the strut under the condition of distorted incoming flow at the inlet. The measured data is input into the algorithm program to obtain the changing trends of the velocity and temperature of the air flow along the radial direction. Then, according to the radial grading of the nozzles at the trailing edge of the strut, the air flow rate of each stage is calculated, and the fuel flow rate of each stage is obtained based on the oil-gas matching, that is, the oil-gas ratio of each stage is consistent with the total oil-gas ratio. The nozzles are connected to the mass flow controllers, and the fuel flow rate data of each stage is input into the mass flow controllers, which automatically control the nozzles to inject fuel, realizing radial grading fuel supply for the strut, making the fuel concentration distribution behind the strut more uniform, and improving the combustion efficiency and combustion stability.

[0041] The above are only the preferred embodiments of the present invention. It should be pointed out that any simple modification, equivalent change and modification made to the above embodiments based on the technical essence of the present invention still belong to the technical and protection scope of the present invention.

Claims

1. An intelligent adjustment technology for oil-gas matching adapting to inlet distortion, characterized in that It includes the following contents: Under the condition of distorted incoming flow at the inlet, by arranging multiple temperature and pressure measurement points at the leading edge of the strut (1), the pressure and temperature parameters of the incoming flow are measured. Combining with the inlet static pressure, the measured data is input into the algorithm program to obtain the velocity distribution trend of the air flow along the radial direction; According to the radial grading of the nozzles (2) at the trailing edge of the strut, the air flow rate of each stage is calculated, and the fuel flow rate of each stage is obtained based on the fuel-gas matching, that is, the fuel-gas ratio of each stage is consistent with the total fuel-gas ratio; Multiple stages of fuel nozzles are arranged in a staggered manner at the trailing edge of the strut. After passing through the fuel supply pipe (3), the nozzles are connected to the mass flow controller. The required fuel flow rate of each stage is input into the mass flow controller to control the fuel injection, realizing the fuel-gas matching under the intake distortion, making the fuel concentration distribution behind the strut more uniform, and improving the combustion efficiency and combustion stability of the afterburner.

2. An intelligent adjustment technology for oil-gas matching adapting to inlet distortion according to claim 1, characterized in that, The length direction of the strut (1) is consistent with the incoming flow direction, and one end located upstream in the length direction of the strut (1) forms its leading edge end face, and the end located downstream forms the trailing edge end face of the strut (1).

3. An intelligent adjustment technology for oil-gas matching adapting to inlet distortion according to claim 1, characterized in that, A plurality of temperature and pressure measurement points are uniformly arranged along the radial direction of the strut (1), and the pressure and temperature parameters of the incoming flow can be measured simultaneously. Among them, the thermocouple wire (7) is fixed in the temperature / pressure measurement channel (4), and the extended part length is used to measure the incoming flow temperature, and the other end is connected to the temperature measurement device through the compensating wire (5); after the total pressure measurement point (8) measures the total pressure of the incoming flow, the total pressure pipe (6) is connected to the pressure measurement device.

4. An intelligent adjustment technology for oil-gas matching with adaptive inlet distortion according to claim 1, characterized in that, Four stages of fuel nozzles (2) are arranged in a staggered manner at the trailing edge of the strut (1). The nozzles are uniformly distributed along the height direction of the strut and are divided into four regions. Each region contains four nozzles, forming a radial grading. The nozzles are connected to the fuel supply pipe (3), and the other end of the nozzles is connected to the mass flow controller, and the fuel injection of the nozzles is automatically adjusted by the mass flow controller.

5. An intelligent adjustment technology for oil-gas matching with adaptive inlet distortion according to claim 4, characterized in that The nozzles of each stage are arranged in a staggered manner, and the fuel supply pipe is located between two nozzles on the same side, ensuring that the fuel injection amounts of the two nozzles are the same; the mass flow controller of each stage can independently adjust the fuel flow rate. The mass flow controller has the ability of rapid response, can complete the adjustment quickly, and has high precision and high reliability.

6. An intelligent adjustment technology for oil-gas matching adapting to inlet distortion according to claim 1, characterized in that The whole strut (1) is symmetric about the left and right sides in its width direction. The nozzles at the trailing edge of the strut are arranged in a staggered manner and can be divided into multiple regions to form a radial grading. The spacing between the nozzles and the number of radial grading are not limited and can be graded according to actual needs.

7. An intelligent regulation technology for oil-gas matching with self-adaptive inlet distortion according to claim 1, characterized in that To cope with different distorted incoming flow conditions, referring to the data measured at the leading edge of the strut, the velocity distribution trend of the air flow along the radial direction is obtained through the algorithm program as shown in Equation (1). Then, according to the radial grading of the nozzles at the trailing edge of the strut, the air flow rate of each stage is calculated as shown in Equation (2), and the fuel flow rate of each stage is obtained based on the fuel-gas matching, that is, the fuel-gas ratio of each stage is consistent with the total fuel-gas ratio as shown in Equation (3); v = f(p, p0, T) (1) m i,air = f(v, ρ, A) (2) m i,f = α * m i,air = f(α, v, ρ, A) (3) where p is the static pressure of the incoming flow, p0 is the total pressure at the leading edge of the strut, T is the total temperature at the leading edge of the strut, v is the radial velocity of the strut, A is the cross-sectional area of the incoming flow, ρ is the air density, m i,air is the air flow rate per stage, and m i,f is the fuel flow rate per stage, and α is the air-fuel ratio.

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