CN105067268A - Turbine-piston combined cycle engine ejection system - Google Patents
Turbine-piston combined cycle engine ejection system Download PDFInfo
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- CN105067268A CN105067268A CN201510478896.9A CN201510478896A CN105067268A CN 105067268 A CN105067268 A CN 105067268A CN 201510478896 A CN201510478896 A CN 201510478896A CN 105067268 A CN105067268 A CN 105067268A
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- cycle engine
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Abstract
The invention provides a turbine-piston combined cycle engine ejection system, which comprises an ejector, an auxiliary combustion chamber and a pressurizer, wherein the front end of the ejector is connected with a gas compressor outlet of the pressurizer, the rear end of the ejector is connected with the front end of the auxiliary combustion chamber, the rear end of the auxiliary combustion chamber is connected with a turbine inlet of the pressurizer, and the front end of the auxiliary combustion chamber is connected with the gas compressor outlet of the pressurizer; and part of the gas at the gas compressor outlet of the pressurizer is guided into the ejector and the auxiliary combustion chamber, so as to form pressure difference between the gas compressor outlet and the turbine inlet gradually. The turbine-piston combined cycle engine ejection system has the advantages of filling in a gap of low-speed starting of a turbine-piston combined cycle engine simulation verification system, satisfying ignition requirement of the auxiliary combustion chamber of the cycle engine and starting requirement of a power turbine, further studying the combined cycle process of a diesel engine and the power turbine, and achieving the test verification of the turbine-piston combined cycle engine.
Description
Technical field
The invention belongs to technical field of engines, especially relate to a kind of Turbine piston combined cycle engine ejection system.
Background technology
The development of ground force's weaponry in modern war, more and more higher to the performance requirement of armored fighting vehicle engine.Need engine can provide when vehicular weapons system works the power that significantly overflows.Turbine piston combined cycle starts function to meet the power requirement that overflows to power train in vehicle application such as high energy armament systems.
Carry out verification experimental verification research by Turbine piston combined cycle simulation of engine verification system, for resolution system is difficult to the problem of low speed starting, need to set up a kind of injection backup system and start to realize low speed.
Summary of the invention
In view of this, the present invention is intended to propose a kind of Turbine piston combined cycle engine ejection system, to solve the problem that Turbine piston combined cycle engine is difficult to low speed starting.
For achieving the above object, technical scheme of the present invention is achieved in that
A kind of Turbine piston combined cycle engine ejection system, comprise injector, auxiliary combustion chamber and supercharger, the front end of described injector connects the blower outlet of supercharger, injector rear end connects the front end of auxiliary combustion chamber, described auxiliary combustion chamber rear end is connected with the turbine inlet of supercharger, and auxiliary combustion chamber front end also connects the blower outlet of supercharger; Under the effect of the nozzle drainage of injector, a part of gas of the blower outlet of supercharger is directed into injector and auxiliary combustion chamber, and progressively make blower outlet and turbine inlet mineralization pressure poor.
Further, described injector is primarily of nozzle, nozzle pipeline, introduction pipeline and mixed pipe line composition, and described nozzle is arranged in nozzle pipeline, and nozzle pipeline side arranges introduction pipeline, and the output terminal of nozzle pipeline is mixed pipe line; Described nozzle pipeline, introduction pipeline are all consistent with the line cross section of mixed pipe line.
Further, the end face cross-sectional area of the pipeline of described injector is 4.5 times of nozzle face cross-sectional area.
Further, the pipeline end face cross-sectional area of described injector is 2 times of the cross-sectional area of mixed pipe line and nozzle pipeline intermediate duct contraction place.
Further, the angle of the central shaft of the nozzle of described injector and the central shaft of introduction pipeline is 40 degree.
Further, the sidewall of the nozzle of described injector and the angle of axis are 6 degree.
Relative to prior art, the present invention has following advantage:
(1) the present invention compensate for the blank that Turbine piston combined cycle simulation of engine verification system low speed starts, the igniting of the auxiliary combustion chamber of combined cycle engine and the start request of power turbine can be met by native system, the combined cycle process of diesel engine and power turbine can be furtherd investigate, realize the verification experimental verification of Turbine piston combined cycle engine, for following new type power research lays the foundation;
(2) present system structure is simple, and easily realize, cost of manufacture is low, can wide popularization and application.
Accompanying drawing explanation
The accompanying drawing forming a part of the present invention is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structure principle chart of the ejection system described in the embodiment of the present invention;
Fig. 2 is the structural drawing of the injector described in the embodiment of the present invention.
Description of reference numerals:
1-injector, 2-auxiliary combustion chamber, 3-supercharger, 4-nozzle, 5-introduction pipeline, 6-mixed pipe line, 7-nozzle pipeline.
Embodiment
It should be noted that, when not conflicting, the embodiment in the present invention and the feature in embodiment can combine mutually.
Below with reference to the accompanying drawings and describe the present invention in detail in conjunction with the embodiments.
A kind of Turbine piston combined cycle engine ejection system, as shown in Figure 1, comprise injector 1, auxiliary combustion chamber 2 and supercharger 3, the front end of described injector 1 connects the blower outlet of supercharger 3, injector 1 rear end connects the front end of auxiliary combustion chamber 2, described auxiliary combustion chamber 2 rear end is connected with the turbine inlet of supercharger 3, and auxiliary combustion chamber 2 front end also connects the blower outlet of supercharger 3.
Injector of the present invention forms primarily of nozzle 4, nozzle pipeline 7, introduction pipeline 5 and mixed pipe line 6, and as shown in Figure 2, described nozzle 4 is arranged in nozzle pipeline 7, and nozzle pipeline 7 side arranges introduction pipeline 5, and the output terminal of nozzle pipeline 7 is mixed pipe line 6; Nozzle pipeline 7 of the present invention, introduction pipeline 5 are all consistent with the line cross section of mixed pipe line 6, and pipeline diameter is D1, and D1 is 100 millimeters; The D2 of the end face diameter of nozzle 4; The end face of described nozzle 4 is 190 millimeters to the length L3 of the end face of mixed pipe line 6, and the end face of described mixed pipe line 6 is 140 millimeters to the length L2 of the xsect with nozzle pipeline 7 intermediate duct contraction place; The intersection point of described introduction pipeline 5 axis and nozzle pipeline 7 axis is 40 millimeters to the length L1 of nozzle 4 end face.
The pipeline end face cross-sectional area of injector 1 of the present invention is 4.5 times of nozzle 4 end face cross-sectional area; The pipeline end face cross-sectional area of described injector 1 is 2 times of the cross-sectional area of mixed pipe line 6 and nozzle pipeline 7 intermediate duct contraction place; The angle α of nozzle 4 central shaft of described injector 1 and the central shaft of introduction pipeline 5 is 40 degree; The sidewall of the nozzle 4 of described injector 1 and the angle β of axis are 6 degree.The preferred above-mentioned size of present system injector is arranged, and injection effect is best.
The present invention is under the effect of the nozzle drainage of injector 1, a part of gas of the blower outlet of supercharger 3 is directed into injector 1 and auxiliary combustion chamber 2, and progressively make blower outlet and turbine inlet mineralization pressure poor, supercharger 3 rotating speed improves constantly, system capacity loss reduces, and guarantees that auxiliary combustion chamber 2 does not stop working under the outer gas source feed of system shutdown is transferred to self-loopa state.
The effect of ejection system of the present invention is to be flowed along correct direction by the bootable pneumatic plant gas of the drainage of the nozzle 4 of injector 1, prevent gas backflow, the rotating speed accelerating supercharger 3 rises, and reduces system capacity loss, guarantees Turbine piston combined cycle engine Fast starting.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (6)
1. a Turbine piston combined cycle engine ejection system, it is characterized in that: comprise injector (1), auxiliary combustion chamber (2) and supercharger (3), described injector (1) front end connects the blower outlet of supercharger (3), injector (1) rear end connects the front end of auxiliary combustion chamber (2), described auxiliary combustion chamber (2) rear end is connected with the turbine inlet of supercharger (3), and auxiliary combustion chamber (2) front end also connects the blower outlet of supercharger (3).
2. Turbine piston combined cycle engine ejection system according to claim 1, it is characterized in that: described injector forms primarily of nozzle (4), nozzle pipeline (7), introduction pipeline (5) and mixed pipe line (6), described nozzle (4) is arranged in nozzle pipeline (7), nozzle pipeline (7) side arranges introduction pipeline (5), and the output terminal of nozzle pipeline (7) is mixed pipe line (6); Described nozzle pipeline (7), introduction pipeline (5) are all consistent with the line cross section of mixed pipe line (6).
3. Turbine piston combined cycle engine ejection system according to claim 2, is characterized in that: the line cross section of described injector (1) amasss 4.5 times of the end face cross-sectional area into nozzle (4).
4. Turbine piston combined cycle engine ejection system according to claim 2, is characterized in that: the pipeline end face cross-sectional area of described injector (1) is 2 times of the cross-sectional area of mixed pipe line (6) and nozzle pipeline (7) intermediate duct contraction place.
5. Turbine piston combined cycle engine ejection system according to claim 2, is characterized in that: the angle of the central shaft of the nozzle (4) of described injector (1) and the central shaft of introduction pipeline (5) is 40 degree.
6. Turbine piston combined cycle engine ejection system according to claim 2, is characterized in that: the sidewall of nozzle (4) and the angle of axis of described injector (1) are 6 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510478896.9A CN105067268A (en) | 2015-08-06 | 2015-08-06 | Turbine-piston combined cycle engine ejection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510478896.9A CN105067268A (en) | 2015-08-06 | 2015-08-06 | Turbine-piston combined cycle engine ejection system |
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| Publication Number | Publication Date |
|---|---|
| CN105067268A true CN105067268A (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510478896.9A Pending CN105067268A (en) | 2015-08-06 | 2015-08-06 | Turbine-piston combined cycle engine ejection system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610331A (en) * | 2020-12-16 | 2021-04-06 | 中国人民解放军国防科技大学 | Negative pressure adjustable injection type compressor simulation test device |
Citations (5)
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|---|---|---|---|---|
| CN2160898Y (en) * | 1993-07-17 | 1994-04-06 | 中国兵器工业第七○研究所 | Gas-turbine type pressurizer run-in stand |
| WO2001016471A1 (en) * | 1999-09-01 | 2001-03-08 | Siemens Aktiengesellschaft | Method and device for increasing the pressure of a gas |
| JP2008096111A (en) * | 2006-10-05 | 2008-04-24 | Toyo Eng Works Ltd | Environmental test device of engine for mobile vehicle |
| CN102128079A (en) * | 2011-02-22 | 2011-07-20 | 孙敏超 | Injection/drainage air-supply turbocharging system |
| CN103670626A (en) * | 2013-12-27 | 2014-03-26 | 天津大学 | Two-stage expansion jet type waste heat recovery system of internal combustion engine |
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2015
- 2015-08-06 CN CN201510478896.9A patent/CN105067268A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2160898Y (en) * | 1993-07-17 | 1994-04-06 | 中国兵器工业第七○研究所 | Gas-turbine type pressurizer run-in stand |
| WO2001016471A1 (en) * | 1999-09-01 | 2001-03-08 | Siemens Aktiengesellschaft | Method and device for increasing the pressure of a gas |
| JP2008096111A (en) * | 2006-10-05 | 2008-04-24 | Toyo Eng Works Ltd | Environmental test device of engine for mobile vehicle |
| CN102128079A (en) * | 2011-02-22 | 2011-07-20 | 孙敏超 | Injection/drainage air-supply turbocharging system |
| CN103670626A (en) * | 2013-12-27 | 2014-03-26 | 天津大学 | Two-stage expansion jet type waste heat recovery system of internal combustion engine |
Non-Patent Citations (2)
| Title |
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| 孟令广等: "涡轮增压器自循环低周疲劳试验装置", 《实验技术与管理》 * |
| 黄佑生等: "利用空气引射方案改善涡轮增压柴油机加速性的研究", 《内燃机学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610331A (en) * | 2020-12-16 | 2021-04-06 | 中国人民解放军国防科技大学 | Negative pressure adjustable injection type compressor simulation test device |
| CN112610331B (en) * | 2020-12-16 | 2021-12-31 | 中国人民解放军国防科技大学 | Negative pressure adjustable injection type compressor simulation test device |
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Application publication date: 20151118 |