CN109668739B - Test platform for multi-duct turbine nozzle integrated research - Google Patents
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Abstract
The invention discloses a test platform for integrated research of a multi-duct turbine nozzle, which comprises an air inlet section, a turbine section, an outer duct, a third duct air inlet system and a nozzle section, wherein the problem of mixing of the turbine, the nozzle and the inner and outer ducts is integrally researched; an electric heater is arranged in front of the air inlet volute, so that the total temperature difference between the main flow and the bypass fluid is less than or equal to 300K; in order to better simulate the mixing between the inner culvert airflow and the outer culvert airflow, a lobe ejector is arranged at the outlet of the turbine section; the outer culvert inlet is positioned above the ejector and at the spray pipe inlet, and the spray pipe inlet is provided with a mixing section which is approximately equal to straight; the third duct is positioned between the throat and the outlet of the spray pipe, the inlet areas of the external duct and the third duct are adjustable, and the duct ratio is changed within the range of 0-1.0. The invention provides a multi-duct turbine nozzle integrated test research platform structure frame aiming at the structural characteristics of a multi-duct self-adaptive engine turbine nozzle, which is used for researching the mutual influence and matching relationship of the turbine nozzles in a multi-duct engine and mastering the pneumatic and stealth performance of the multi-duct lower nozzle.
Description
Technical Field
The invention relates to a test platform for multi-duct turbine nozzle integrated research, and belongs to the technical field of impeller machinery.
Background
An Adaptive Cycle Engine (ACE) automatically changes the flow and pressure ratio of a fan and a core Engine by changing the positions of a plurality of adjustable geometric mechanisms and adopting an Adaptive control technology according to different mission requirements of an airplane, so that the Engine obtains the optimal performance at different speeds and heights in an envelope, and the combined performance with the airplane is optimal, and the ACE is an advanced variable Cycle Engine. The aircraft engine has the advantages of good comprehensive performance in the envelope, low oil consumption, long aircraft range, automatic matching of air inlet flow, good flying/generating combination performance, good stealth performance, benefit for thermal management design and the like, and is highly valued by advanced countries in the world. However, the method has the technical difficulties of multiple working modes, complex state conversion, multiple adjustable components, complex mechanism, wide adjustment range, multiple adjustable variables and the like, and the research difficulty is very high. In 2012 to 2016, the U.S. air force organization invests about 6.85 hundred million dollars, and an AETD plan is developed on the basis of ADVENT research, so as to promote the maturity of an adaptive engine technology adopting a 3-runner structure and provide power for various combat platforms such as the next generation fighter or bomber of the U.S. air force. 2016, 6 and 30 months and expected to be 10 years, the United states air force invests 20 hundred million dollars in capital investment, AETP research program is developed, and technical development and verification are undertaken by GE and PW companies. The AETP plan will continue to work along the basic feasibility of the adaptive cycle verified by the ATED research plan, and realize the smooth transition of the 3-channel adaptive engine from the technical prototype to the engineering verifier, with the following aims: compared with the prior art, the fuel efficiency of the engine is improved by 25%, the thrust is increased by 10%, and the fighting range is prolonged by 30%.
The 3-flow channel configuration can provide 1 flow of relatively low temperature air for signal management relative to a conventional turbofan aircraft engine, which means that excess air can be used to cool hot end components to reduce ir signals, or into the core engine and afterburner to increase thrust. Because the structure is complicated, the manufacturing difficulty is big, and the researchers in China mostly start from variable geometry spray tube alone, assume that the spray tube import mixes evenly, through adjusting spray tube throat area and molded lines, experimental and numerical simulation spray tube control law. But the outlet of the turbine has rotational flow and has strong mixing with the bypass airflow, so that the turbine/nozzle integrated research improves the turbine performance, increases the mixing of the inner and outer ducts, shortens the length of the nozzle and improves the stealth effect of the nozzle. Especially for 3-channel structures, the influence of the bypass airflow on the nozzle performance must be considered.
Therefore, the invention provides an integrated test research platform for a multi-duct turbine nozzle, aiming at the next generation of self-adaptive engines, and comprehensively considering the high efficiency and good stealth performance of the design and research of an exhaust system by mixing the rotational flow at the outlet of a turbine and a bypass and the airflow of a third duct.
Disclosure of Invention
The purpose of the invention is as follows: in order to research the pneumatic problem existing in the next generation of self-adaptive multi-duct engine exhaust system, the invention provides a test platform for the integrated research of a multi-duct turbine nozzle, which is used for researching the regulation rule of the exhaust system with the mixing of an internal duct and an external duct and the duct ratio in the range of 0-1.0, carrying out deep research on the pneumatic problem in the exhaust system and providing a technology and a test support for the development of the self-adaptive engine.
The technical scheme is as follows: in order to achieve the purpose, the invention adopts the technical scheme that:
a test platform for multi-duct turbine nozzle integrated research comprises the following structures:
an air inlet section: the air inlet of the air inlet volute is connected with a high-pressure air source through an electric heater, the main flow is heated through the electric heater, the total temperature difference between the main flow and the bypass airflow is guaranteed to be less than or equal to 300K, and the heated main flow gas is conveyed to the turbine section through the air inlet volute;
a turbine section: the jet-type turbine comprises an inlet guide vane, a rotor, an outlet guide vane and a central cone, wherein an ejector is arranged at an outlet of a turbine section and used for increasing mixing between bypass airflow and main flow gas at the outlet of the turbine, and the main flow gas is conveyed to a jet pipe section through the ejector;
outer culvert and third duct air system, spout the pipeline section: the inlet of the outer duct is arranged at the inlet of the spray pipe above the ejector, the inlet of the spray pipe is provided with a mixing section which is approximately equal to straight, and the inlet of the third duct is arranged between the throat of the spray pipe and the outlet of the spray pipe; the areas of the inlet of the outer duct and the inlet of the third duct are adjustable, and the total duct ratio is ensured to be 0-1.0.
The invention combines the structural characteristics of a 3-channel self-adaptive engine, combines an air inlet section, a turbine section, a culvert, a third culvert air system and a spray pipe section into a system, heats a main flow through an electric heater, and ensures that the total temperature difference between the main flow and the culvert airflow is less than or equal to 300K; the outlet areas of the outer culvert and the third culvert are adjustable, and the research requirement in the range of 0-1.0 of the culvert ratio is met.
Furthermore, the air inlet section, the outer culvert and the third culvert air system use the same high-pressure air source, and air inlets of the air inlet section, the outer culvert and the third culvert air system are respectively connected with a high-pressure air source valve through high-pressure flow control valves.
Further, the hub ratio of the turbine section is 0.65, and the ratio of the axial length of the turbine section to the length of the spray pipe section is 1: 5.
Further, for better simulating the mixing between inner and outer culvert airflows, the ejector adopts a wave-lobe ejector, and the axial length of the wave-lobe ejector is 35% of the turbine section.
Further, the third duct inlet is located at a position 30-50% between the nozzle throat and the nozzle outlet.
Furthermore, the inlet width of the outer duct inlet and the inlet width of the third duct inlet are controlled by adjusting valves respectively, so that the flow of the outer duct inlet and the flow of the third duct inlet are independently adjusted, and the total duct ratio is ensured to be 0-1.0.
Further, the inlet width adjusting range d of the inlet of the outer ductw1The inlet width adjusting range d of the inlet of the third duct is 0-25 mmw2＝0～20mm。
Has the advantages that: compared with the prior art, the test platform for the multi-duct turbine nozzle integrated research has the following advantages: 1. the turbine outlet rotational flow, the mixing of the inner culvert and the outer culvert and the third culvert airflow are considered in an exhaust system, the structure is relatively simple, and a good main control effect is achieved; 2. the flow of the culvert and the third culvert is independently controlled, and the test platform can carry out research on an exhaust system in the range of 0-1.0 of the total culvert ratio and under different flow distribution ratios of the culvert and the third culvert; 3. the ejector is arranged at the outlet of the turbine, so that the influence of inside and outside culvert mixing on the performance of the spray pipe can be simulated.
Drawings
FIG. 1 is a schematic overall structure diagram of an embodiment of the present invention;
FIG. 2 is a schematic diagram of a laboratory structure according to an embodiment of the present invention;
FIG. 3 is a perspective view of a turbine component in an embodiment of the invention;
FIG. 4 is a perspective view of a lobe injector in accordance with an embodiment of the present disclosure;
FIG. 5 is a perspective view of a nozzle segment, an outer ducted inlet, and a third ducted inlet in an embodiment of the present invention;
the figure includes: 1. the high-pressure gas source comprises a high-pressure gas source valve 2, a high-pressure flow control valve 3, a high-pressure flow control valve 4, an electric heater 5, a gas inlet volute 6, an inlet guide vane 7, a rotor 8, a rotor rotating shaft 9, an outlet guide vane 10, a central cone 11, an ejector 12, an outer duct inlet 13, a third duct inlet 14, a spray pipe throat 15, a mixing section 16, an adjusting valve 17, an exhaust silencer 18, a vortex dynamometer 19, flow field measuring equipment 20 and a master control room.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and examples.
As shown in FIG. 1, the test platform for the multi-duct turbine nozzle integrated research mainly comprises:
an air inlet section: the gas inlet of the gas inlet volute 5 is connected with the high-pressure gas source 1 through the electric heater 4, the main flow is heated through the electric heater 4, the total temperature difference between the main flow and the bypass gas flow is guaranteed to be less than or equal to 300K, the main flow is used for researching the influence on the mixing process under different temperature differences, and the heated main flow gas is conveyed to a turbine section through the gas inlet volute 5;
a turbine section: the device comprises an inlet guide vane 6, a rotor 7, an outlet guide vane 9 and a central cone 10, wherein an ejector 11 is arranged at an outlet of a turbine section and used for increasing mixing between bypass airflow and main flow gas at an outlet of the turbine, and the main flow gas is conveyed to a jet pipe section 14 through the ejector 11;
outer culvert and third culvert air system, jet pipe section 14: the outer duct inlet 12 is arranged at the inlet of a spray pipe section 14 above the ejector 11, the inlet of the spray pipe section 14 is provided with a mixing section 15 which is approximately equal to straight, and the third duct inlet 13 is arranged between the throat of the spray pipe and the outlet of the spray pipe; the bypass inlet 12 and the third bypass inlet 13 respectively control the inlet width through an adjusting valve 16, so that the flow of the bypass inlet 12 and the third bypass inlet 13 can be independently adjusted, and the total bypass ratio is ensured to be 0-1.0.
In consideration of the structural size and the test requirements, the turbine section adopts a 1.5-stage turbine (as shown in fig. 3) which comprises an inlet guide vane, a rotor, an outlet guide vane and a central cone and is used for researching the flow field structure of a blending section under the inlet cyclone and the influence of the flow field structure on a jet pipe section. The preferred design is as follows: the turbine inlet flow is 5kg/s, the rotating speed is 3000rpm, and the pressure drop ratio is 1.35; the third-order Bezier curve is adopted to design turbine parts, and the outer diameter D of the inlet guide vane is preferentially determinedS0.4m, inner diameter DhThe number of the inlet guide vane, the rotor and the outlet support plate is respectively 24, 39 and 7, and the outlet guide vane is a force bearing component of the rotor. The central cone can be a blunt-end short cone or a pointed-end long cone according to different study objects.
The ejector is arranged at the outlet of the turbine section and used for increasing the mixing between the bypass airflow and the main flow gas at the outlet of the turbine and approximately simulating the mixing of the bypass airflow and the main flow gas in a real engine, and the geometrical configuration of the ejector is a circular truncated cone shape, a protruding piece, a wave lobe shape and the like. As shown in fig. 4, in order to better simulate the mixing between the inner and outer culvert airflows, the ejector in this embodiment adopts a lobe type ejector, and 12 "lobes" are uniformly distributed for a circle, and each "lobe" is composed of two circular arcs and two straight lines.
As shown in FIG. 5, the culvert outlet is located at the inlet of the air inlet section and the inlet of the nozzle, the inlet of the nozzle is provided with a mixing section which is approximately equal to straight and is used for mixing the culvert air flow, and the outlet width adjusting range dw10-25 mm; the third duct is positioned between the throat and the outlet of the spray pipe, about 50 percent of the position and the width adjusting range d of the outletw20-20 mm; the air inlet section, the culvert and the third culvert air system adopt the same high-pressure air source, can heat the main stream according to the requirement of actual problems, and simulate the temperature difference of the culvert air flow under the real environment.
In this embodiment, the hub ratio of the turbine section is 0.65, the ratio of the axial length of the turbine section to the ejector section 14 is 1:5, and the axial length of the lobe ejector is 35% of that of the turbine section.
Aiming at the aerodynamic problems of turbines and spray pipes under multiple ducts, the invention provides an integrated test research platform, can realize the change of the duct ratio within the range of 0-1.0, and has the outstanding characteristics of clear structure, clear research target and the like.
Under the condition that the total flow of a high-pressure air source is 10kg/s, a multi-bypass turbine/spray pipe integrated test platform is designed, in order to meet the requirement that the change range of the bypass ratio is 0-1.0, the flow of a design point of an inlet of a turbine section is set to be 5kg/s, the design of the turbine section is completed by adopting a three-order Beizer curve, an outlet ejector, an outer bypass, a third bypass and a spray pipe section are sequentially designed according to the size of a turbine part, and the specific structural size of the integrated test platform is determined.
The layout structure of the multi-duct turbine/nozzle pipe integrated test chamber is shown in fig. 2, in order to ensure the reliability of test measurement, a rotor rotating shaft 8 is connected with a vortex dynamometer 18 to ensure the stable output power of a turbine, the outlet of a nozzle is connected with an exhaust silencer 17 to reduce the outlet noise, a flow field measuring device 19 can be selected according to the specific requirements of test measurement, the rotor rotating speed, the flow valve control and the data processing are carried out in a master control chamber 20, and the specific test steps are as follows:
1. the method comprises the steps of ensuring that the multi-duct turbine/spray pipe integrated test bed is reliable in connection and the tightness of pipelines, valves and the like meets index requirements, checking the high-pressure gas tank 1, and opening the high-pressure gas source valve 2 if the pressure of the high-pressure gas tank 1 is within a proper range;
2. switching on the power supply of the electric heater 4 and the power supply of the eddy current dynamometer 18, opening the flow control valve 3 of the main bypass, and automatically adjusting the control valve 3 to ensure that the flow of the main bypass is about 5 kg/s;
3. the power of the electric heater 4 and the rotating speed of the rotor rotating shaft 8 are gradually increased, the total temperature of the high-pressure airflow is increased by about 100K-300K (the condition that the turbine inlet temperature is overhigh to cause that the output power of the turbine exceeds the maximum power of the vortex dynamometer) and the rotating speed of the rotor rotating shaft is increased and kept at the rated rotating speed of 3000 rpm;
4. when the flow of the main bypass is stabilized at 5kg/s (+ -0.2 kg/s), the power of the electric heater is 4, the output power is stable (500-1500 kw, determined by test conditions), the rotating speed of the rotor is 3000rpm, and flow field data of the turbine section and the spray pipe section, including parameters such as total temperature, total pressure and airflow angle of the inlet and the outlet of the turbine section and the spray pipe section, are recorded by the flow field measuring equipment 19 under the condition of no influence of bypass airflow;
5. keeping the flow of the main culvert basically stable, opening a main flow valve 3 of an air inlet channel, opening and adjusting an adjusting valve 16 of an inlet 12 of an outer culvert, gradually increasing the flow of the inlet 12 of the outer culvert by 0-3 kg/s, keeping the flow of the outer culvert constant at 3kg/s (+ -0.2 kg/s), keeping the dynamic change process of the flow of the outer culvert for about 3min, and recording dynamic and steady-state flow field data by using a flow field measuring device 19;
6. keeping the flow of the main culvert and the flow of the external culvert basically stable, opening and adjusting an adjusting valve 16 of a third culvert inlet 13, gradually increasing the flow of the third culvert inlet 13 by 0-2 kg/s, keeping the flow of the third culvert constant at 2kg/s (+/-0.1 kg/s), keeping the dynamic change process of the flow of the third culvert at about 3min, and recording dynamic and stable flow field data by using a flow field measuring device 19;
7. the single multi-duct turbine/nozzle integrated test process is about 20min, the flow field data measurement process is about 15min, the adjusting valves 16 of the outer duct and the third duct, the main air inlet channel flow valve 3, the power supply of the electric heater 4, the main duct flow valve 3, the power supply of the vortex dynamometer 18 and the high-pressure air source valve 2 are closed in sequence after the test measurement is completed, and the single multi-duct turbine/nozzle integrated test is finished.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (5)
1. The utility model provides a test platform that is used for many ducts turbine nozzle integration research which characterized in that includes:
an air inlet section: the high-pressure gas turbine comprises a gas inlet volute (5), an electric heater (4) and a high-pressure gas source (1), wherein a gas inlet of the gas inlet volute (5) is connected with the high-pressure gas source (1) through the electric heater (4) and is used for heating a main flow, the total temperature difference between the main flow and a bypass gas flow is ensured to be less than or equal to 300K, and the heated main flow gas is conveyed to a turbine section through the gas inlet volute (5);
a turbine section: the device comprises an inlet guide vane (6), a rotor (7), an outlet guide vane (9) and a central cone (10), wherein an ejector (11) is arranged at an outlet of a turbine section and used for increasing mixing between bypass airflow and main flow gas at an outlet of the turbine, and the main flow gas is conveyed to a jet pipe section through the ejector (11);
a spray pipe section: comprises a spray pipe inlet, a spray pipe throat (14) and a spray pipe outlet which are communicated in sequence, wherein the spray pipe inlet is provided with an equal-straight mixing section (15);
outer culvert and third duct air system: the device comprises an outer duct inlet (12) arranged on the side wall of the inlet of the spray pipe and a third duct inlet (13) arranged on the side wall between the throat (14) of the spray pipe and the outlet of the spray pipe, wherein the areas of the outer duct inlet (12) and the third duct inlet (13) are adjustable, and the total duct ratio is ensured to be 0-1.0;
the outer duct inlet (12) and the third duct inlet (13) are communicated with an air inlet channel, and the high-pressure air source (1) is communicated with the electric heater (4) and the air inlet channel through the high-pressure flow control valve (3) respectively; the outer bypass inlet (12) and the third bypass inlet (13) are respectively provided with an adjusting valve (16), and the flow of the outer bypass inlet (12) and the flow of the third bypass inlet (13) are independently adjusted through the adjusting valves (16);
the test platform further comprises a vortex dynamometer (18) connected with the rotor rotating shaft (8), an exhaust silencer (17) connected with the outlet of the spray pipe, flow field measuring equipment (19) arranged in the spray pipe section and the turbine section and a master control chamber (20), wherein the master control chamber (20) is in signal connection with the high-pressure flow control valve (3), the electric heater (4), the regulating valve (16), the ejector (11), the rotor rotating shaft (8), the vortex dynamometer (18) and the flow field measuring equipment (19).
2. The test platform for the integrated research of the multi-duct turbine nozzle as claimed in claim 1, wherein the hub ratio of the turbine section is 0.65, and the axial length ratio of the turbine section to the nozzle section is 1: 5.
3. The test platform for the integrated research of the multi-duct turbine nozzle as claimed in claim 1, wherein the ejector (11) is a wave-lobe ejector, and the axial length of the wave-lobe ejector is 35% of the turbine section.
4. Test platform for multi-duct turbine nozzle integration studies according to claim 1, characterized in that said third duct inlet (13) is located 30-50% between the nozzle throat (14) and the nozzle outlet.
5. The test platform for the integrated research of the multi-duct turbine nozzle as claimed in claim 1, wherein the inlet width of the outer duct inlet (12) is adjusted within a range of 0-25 mm, and the inlet width of the third duct inlet (13) is adjusted within a range of 0-20 mm.
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| CN112683943B (en) * | 2020-12-01 | 2021-11-16 | 西安交通大学 | Turbine experimental apparatus with adjustable pitch |
| CN112577755B (en) * | 2020-12-11 | 2022-04-19 | 中国科学院工程热物理研究所 | Turbine hub sealing experimental device considering upstream unsteady effect |
| CN112945306B (en) * | 2021-02-05 | 2022-06-07 | 中国航发沈阳发动机研究所 | Test platform for simultaneously measuring thrust and flow of double-duct spray pipe |
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| CN116380472B (en) * | 2023-06-05 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Air inlet device in large bypass ratio engine core engine test |
| CN117848729B (en) * | 2024-03-08 | 2024-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | Double culvert air suction type negative pressure test device |
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| DE69701050T2 (en) * | 1991-07-26 | 2000-08-03 | Galbraith Eng Pty Ltd | Dynamometer with a coupling device for a power tool |
| CN201653700U (en) * | 2010-04-22 | 2010-11-24 | 浙江大学 | Exhaust-reflux electric heating turbine performance test system |
| CN201885874U (en) * | 2010-12-10 | 2011-06-29 | 佳木斯大学 | Engine performance test stand |
| CN102635578A (en) * | 2011-12-23 | 2012-08-15 | 南京航空航天大学 | Multilevel lobed nozzle ejector with secondary-fluid sucking function |
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| CN103835836B (en) * | 2014-03-10 | 2015-09-09 | 金剑 | The gas turbine that a kind of bypass ratio is controlled |
| CN104833475A (en) * | 2015-05-12 | 2015-08-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Turbine engine jet experiment simulation device |
| CN205449504U (en) * | 2016-04-05 | 2016-08-10 | 吉林大学 | Development engine simulation turbocharging system |
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