CN1789686A - Pulsating flow gas turbine - Google Patents
Pulsating flow gas turbine Download PDFInfo
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- CN1789686A CN1789686A CN 200510132561 CN200510132561A CN1789686A CN 1789686 A CN1789686 A CN 1789686A CN 200510132561 CN200510132561 CN 200510132561 CN 200510132561 A CN200510132561 A CN 200510132561A CN 1789686 A CN1789686 A CN 1789686A
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- gas turbine
- turbine
- firing chamber
- pulsating flow
- flow gas
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Abstract
This invention relates to impulse gas motor, which comprises one machine axle, pressed set and turbine set of the machine axle and the burst chamber between the pressed gas set and turbine set, wherein, the burst chamber entrance is set with gas gate and spray mouth and ignition device set on walls; the gas gate and fuel spray and ignition device uses input signal set on the axle rotation number sensor microprocessor controller working according to ruled time sequence; setting parallel double burst chamber and independent work turbine shaft and independent work turbine set as best scheme.
Description
Technical field
The present invention relates to a kind of gas turbine, relate to a kind of pulsating flow gas turbine particularly.
Background technique
As everyone knows, gas turbine is that a kind of volume is little, efficient is high, simple in structure, can use pluralities of fuel, pollute little hot machine motor, be widely used in a lot of occasions, such as aviation, navigation, generating or the like.
But present gas turbine has a fatal defective, be exactly gas turbine only the design rated revolution be efficiently, in case depart from rated revolution, the decline of efficient is very fast.This has just limited the application area of gas turbine, and in a lot of adaptable fields of other motors, gas turbine is not suitable selection.This field mainly is the field that the requirement revolution often changes, such as automobile, locomotive or the like.
Summary of the invention
The objective of the invention is for remedying above-mentioned defective, a kind of pulsating flow gas turbine that can improve the slow speed performance of proposition.
Pulsating flow gas turbine of the present invention, calm the anger unit and turbines and be connected described firing chamber of calming the anger between unit relief opening and the described turbines suction port that one arbor, shared this arbor are arranged, suction port place in this firing chamber, valve is set, oil nozzle and ignition mechanism are set on this chamber wall.
Pulsating flow gas turbine of the present invention, at least one subsidiary combustion chamber in parallel on described firing chamber, the suction port of described subsidiary combustion chamber and described firing chamber is connected in parallel on the relief opening of the described unit of calming the anger, the relief opening of described subsidiary combustion chamber and described firing chamber is connected in parallel on the suction port of described turbines, and described subsidiary combustion chamber is provided with independently valve, oil nozzle and ignition mechanism.
Because the gas turbine that the control ratio of each valve, oil nozzle and ignition mechanism is general wants complicated, so preferably adopt microprocessor controller control valve, oil nozzle and ignition mechanism, the input revolution signal of this microprocessor controller is taken from the tachometer generator that is arranged on the described arbor.When adopting a plurality of firing chamber, the valve of each firing chamber, oil nozzle and ignition mechanism are controlled with same microprocessor controller.
Pulsating flow gas turbine of the present invention can also be provided with independently work turbine arbor and independently work turbine unit, and the suction port of described work turbine unit is connected through pipeline with the relief opening of described turbines,
Because the gas turbine number of moving part is higher, its output is preferably by big ratio retarder output.This retarder can use general retarder or planet wheel decelerator.Pulsating flow gas turbine of the present invention can be the direct connection reducer of arbor, through reducer output shaft output, also can export through reducer output shaft at the described turbo machine the tip of the axis connection reducer that works alone.
Fig. 1 is the schematic representation of reciprocating engine combustion gas acting, and therefrom as can be seen, for reciprocating engine, because firing chamber three faces all are airtight, the combustion gas acting face in its firing chamber has only piston on one side.And just different in gas turbine, concrete visible Fig. 2 is not a closure at the front end of gas-turbine combustion chamber, but impeller.We know compressor impeller has only just maximum when the rated revolution of design the efficient of calming the anger, and that is to say, only in rated revolution, front end is equivalent to sealing, and the state of combustion gas gas acting and reciprocating engine shown in Figure 1 are similar.If in case report and be lower than rated revolution, the efficient of calming the anger can sharply descend, the front end of firing chamber with regard to inequivalence in sealing.This moment, combustion gas will inevitably leak from front end, and the combustion gas that the back turbine is done manual work will reduce; Although in this case, turbine can drive compression impellor and improve revolution, and before revolution was not raised to rated revolution, leakage still was unavoidable.So when non-rated revolution, combustion gas are far smaller than rated revolution to the work doing efficiency of turbine.This reason causes gas turbine when non-rated revolution just, and the decline of efficient is higher than reciprocating engine far away.
Core of the present invention is that the front end in the firing chamber increases dividing plate and valve to be opened/closed, and the mixed gas in the firing chamber is burning expansion when valve-closing, even like this in non-rated revolution, combustion gas also can do work to turbine with all strength.
Pulsating flow gas turbine of the present invention can improve the working pressure of combustion temperature and output turbine, has also just improved delivery efficiency, adopts intermittent combustion simultaneously, can the fuel saving consumption; Firing chamber and turbo machine are in the discontinuous operation state, and non-period of combustion, section had pressurized air to flow through in the same old way, can guarantee the cooling of firing chamber and turbine when improving combustion temperature like this; This pulsating flow gas turbine starts easily, and the application of twin shaft scheme has further improved the slow speed performance.
Description of drawings
Fig. 1 is a reciprocating engine combustion gas acting schematic representation;
Fig. 2 is a gas turbine combustion gas acting schematic representation;
Fig. 3 is a pulsed combustion gas wheel wheel single combustion chamber schematic representation of the present invention;
Fig. 4 is a pulsating flow gas turbine of the present invention double combustion chamber single shaft schematic representation;
Fig. 5 is a pulsating flow gas turbine of the present invention double combustion chamber twin shaft schematic representation.
Embodiment
In order further to illustrate pulsating flow gas turbine of the present invention, illustrate respectively below.
Embodiment 1:
Pulsating flow gas turbine is seen Fig. 3, and the calm the anger unit 1 and the turbines 2 and be connected firing chamber 5 between the suction port 14 of calm the anger unit 1 relief opening 20 and turbines 2 of an arbor 16, shared this arbor 16 arranged; 5 the ingress in the firing chamber is provided with valve 7 to be opened/closed, and oil nozzle 9 and ignition mechanism 18 are set on 5 walls of firing chamber; Arbor 16 connection reducers 4 are through output shaft 13 output, the i.e. shared axles of the output of motor and gas compressor.In the present embodiment, pulsating flow gas turbine adopts automatically controlled mode: in arbor 16 peripheries tachometer generator 15 is set; Other is provided with microprocessor controller, and its input revolution signal is taken from tachometer generator 15, and other signal is taken from revolution and regulated throttle, torque sensor and pressure transducer, its output control valve 7, oil nozzle 9 and ignition mechanism 18.Obviously, pulsating flow gas turbine by above structure fabrication is fully operational in pulse condition, be exactly when valve 7 is opened, the pressurized gas of gas compressor just can enter the firing chamber, after the valve-closing, oil spout forms mixed gas, by the ignition device detonation, and the exhaust of rearward expanding simultaneously, turbine is done work; But because the pressurized air of gas compressor output is exported nowhere when valve-closing, the resistance that this must increase gas compressor lowers efficiency.
Embodiment 2:
Pulsating flow gas turbine of the present invention preferably has the firing chamber of at least two parallel connections, concrete visible Fig. 4.This figure is depicted as a small-power testing machine, and the unit of calming the anger is selected centrifugal-flow compressor for use, and turbines 2 is selected radial-flow turbine for use.
In the firing chamber 5, be arranged in parallel a subsidiary combustion chamber 6, the suction port of subsidiary combustion chamber 6 and firing chamber 5 is connected in parallel on the relief opening 20 of the unit 1 of calming the anger, the relief opening of subsidiary combustion chamber 6 and firing chamber 5 is connected in parallel on the suction port of turbines 2, subsidiary combustion chamber is provided with independently valve 8, oil nozzle 10 and ignition mechanism 19, arbor 16 connection reducers 4 are through output shaft 13 outputs.Valve 7,8, oil nozzle 9,10 and ignition mechanism 18,19 are pressed following sequential alternation:
A) valve 7 is closed (valve 8 unlatchings this moment);
B) oil nozzle 9 oil spouts;
C) ignition mechanism 18 igniting, the mixed gas burning expansion exhaust in the firing chamber 5;
D) valve 8 is closed (valve 7 unlatchings this moment);
E) oil nozzle 10 oil spouts;
F) ignition mechanism 19 igniting, the mixed gas burning expansion exhaust in the firing chamber 6;
G) valve 8 is opened firing chamber 6 scavengings.
Because closing of valve 7, the pressurized gas in the firing chamber 5 is in a kind of temporary turbulent condition, sprays into fuel timely, just can obtain mixed gas.Detonation just takes place after lighting, and one time of pressure can obtain several times ground to be increased.
Because two firing chambers are arranged, and alternation, when the valve 7 of a firing chamber (such as firing chamber 5) is closed, calm the anger the pressurized air of unit 1 then by valve 8 and firing chamber 6, this both had been firing chamber 6 scavengings, can play the effect of cooling combustion chamber 6 again, flow through gas and meet when mixing at the combustion gas of discharging with firing chamber 5, can produce secondary combustion, reduce the harmful matter in the discharging; In the time period that two firing chamber valves are all opened, because the inertia of impeller, pressurized air flows through firing chamber and turbines in the same old way, the length of suitable this time period of adjustment, cooling turbine unit effectively.
As turbine 2, in the present embodiment of single axle, then be in a kind of pulsation working state, the pressure that its groundwork pressure provides for gas compressor, when a combustion chambers burn, on this pressure superposition a zigzag pulsating pressure, thereby obtain the higher air-flow of speed in the ingress of turbine 2.Although this pulse pneumatic is not the optimal selection of turbine, because improving day by day of charging turbine technology still can be designed the turbine of the very high pulsation working state of efficient.
This alternate mode has guaranteed gas compressor all the time than stable status work, and it also is feasible that more firing chamber is set certainly.
In the present embodiment, the gas turbine that the control ratio of each valve, oil nozzle and ignition mechanism is general wants complicated, only uses mechanical type control mode more complicated, control accuracy also not enough.Simultaneously also need to gather the moment of torsion of output shaft, the pressure of firing chamber or the like data in actual use, so adopted microprocessor controller control, valve and oil nozzle all adopt solenoid controlled.The input signal of this microprocessor controller is taken from tachometer generator 15 and speed regulator (throttle) and necessary torque sensor and the pressure transducer that is arranged on the described arbor, sends the control signal of each valve, each oil nozzle and each ignition mechanism by the cycle timesharing according to these signals.As gas turbine, self revolution is very high, can not adopt the mode of revolution control, so control cycle is generally got 1/tens even 1/tens of revolution, arbor commentaries on classics tens commentaries on classics even tens transfer to and are one-period in other words, and two firing chambers are according to this cycle alternation.Under automatically controlled mode, valve adopts solenoid controlled.
Because the gas turbine number of moving part is too high, its output must be by big ratio retarder output.This retarder can use general retarder or planet wheel decelerator.
Present embodiment adopts radial-flow compressor and turbine, but does not mean that the present invention is not suitable for axial-flow compressor or turbine.As for calm the anger unit 1 and turbines 2 is to adopt axial flow or radial-flow type, is all feasible in theory, still adopts the selection principle of general gas turbine to get final product, and is exactly the small-power radial-flow type, the high-power axial flow of using.
Embodiment 3:
Fig. 5 is the schematic representation of the embodiment of the invention 3, present embodiment is a twin axle (or claiming a free axis output) scheme, independently work turbine axle 12 and independently work turbine unit 3 are set outside arbor 16 exactly, the intake duct of work turbine unit 3 is connected with the air outlet flue of described turbines 2, retarder 4 is connected the end of independent arbor 12, still through output shaft 13 outputs.In addition, other is identical with embodiment 2.
In this scheme, turbines 2 only provides power for the unit 1 of calming the anger, and the output of motor is born by work turbine 3.Because output shaft 12 separates with arbor 16, the revolution of output shaft 12 and the unit 1 of calming the anger revolution irrelevant, just can when lower output shaft revolution, provide higher working pressure, thereby improve the output torque and the delivery efficiency of work turbine unit 3 for work turbine unit 3.
In the present embodiment, because expanding gas is except work done in turbines 2, also will work done in work turbine unit 3, and 2 needs of turbines provide power for the unit 1 of calming the anger, so want the work done ratio of reasonable distribution expanding gas in two turbines.The unit 1 of calming the anger adopt centrifugal, when work turbine unit 3 adopts radial turbines, turbines 2 should adopt combined flow turbine, to guarantee that combustion gas is in turbines 2 after the work done, there are enough energy transfer to give work turbine unit 3, certainly in this case, turbines 2 adopts axial-flow turbine also to be fine.
Embodiment's schematic representation provided by the present invention is radial flow impeller, but and does not mean that the present invention only is applicable to radial-flow type.Pulsating flow gas turbine can adopt aial flow impeller equally, or adopts hybrid mode.
The present invention can improve the working pressure of combustion temperature and turbine, has also just improved delivery efficiency, adopts intermittent combustion simultaneously, can the fuel saving consumption; Simultaneously firing chamber and turbo machine are in the discontinuous operation state, and non-period of combustion, section had pressurized air to flow through in the same old way, can guarantee the cooling of firing chamber and turbine when improving combustion temperature like this; This pulsating flow gas turbine starts easily, and the twin shaft scheme can further improve low speed torque.
Claims (7)
1, pulsating flow gas turbine, comprise the unit of calming the anger (1) and the turbines (2) of arbor (16), shared this arbor (16) and be connected the relief opening (20) of the described unit of calming the anger (1) and the suction port (14) of described turbines (2) between firing chamber (5), it is characterized in that suction port place in described firing chamber (5), valve (7) is set, oil nozzle (9) and ignition mechanism (18) are set on the wall of described firing chamber (5).
2, pulsating flow gas turbine according to claim 1, it is characterized in that going up at least one subsidiary combustion chamber (6) in parallel in described firing chamber (5), the suction port of described subsidiary combustion chamber (6) and described firing chamber (5) is connected in parallel on the relief opening (20) of the described unit of calming the anger (1), the relief opening of the relief opening of described subsidiary combustion chamber (6) and described firing chamber (5) is connected in parallel on the suction port (14) of described turbines (2), and described subsidiary combustion chamber (6) is provided with independently valve (8), oil nozzle (10) and ignition mechanism (19).
3, pulsating flow gas turbine according to claim 1, it is characterized in that described valve (7), oil nozzle (9) and ignition mechanism (18) by microprocessor controller control, the input revolution signal of this microprocessor controller is taken from the tachometer generator (15) that is arranged on the described arbor.
4, pulsating flow gas turbine according to claim 2 is characterized in that described valve (7,8), oil nozzle (9,10) and ignition mechanism (18,19) control with same microprocessor controller.
5, according to the described pulsating flow gas turbine of one of claim 1-4, it is characterized in that directly connection reducer (4) of arbor (16), export through reducer output shaft (13).
6, according to the described pulsating flow gas turbine of one of claim 1-4, it is characterized in that being provided with independently work turbine arbor (12) and independently work turbine unit (3), the suction port of described work turbine unit (3) is connected by pipeline with the relief opening of described turbines (2).
7, pulsating flow gas turbine according to claim 6 is characterized in that the described turbine shaft that works alone (12) connection reducer (4), exports through reducer output shaft (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005101325618A CN100365256C (en) | 2005-12-26 | 2005-12-26 | Pulsating flow gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005101325618A CN100365256C (en) | 2005-12-26 | 2005-12-26 | Pulsating flow gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1789686A true CN1789686A (en) | 2006-06-21 |
| CN100365256C CN100365256C (en) | 2008-01-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2005101325618A Expired - Fee Related CN100365256C (en) | 2005-12-26 | 2005-12-26 | Pulsating flow gas turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033248A (en) * | 2014-06-04 | 2014-09-10 | 华能国际电力股份有限公司 | Ground gas turbine utilizing pulse detonation combustion |
| CN113048512A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Fuel grading control assembly, fuel system, gas turbine, override valve and fuel grading control method |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3517679A (en) * | 1968-03-08 | 1970-06-30 | United Aircraft Corp | Dual fluid crossover control |
| GB1217070A (en) * | 1968-07-17 | 1970-12-23 | Rolls Royce | Improvements in or relating to gas turbine engines |
| GB1371097A (en) * | 1971-10-06 | 1974-10-23 | Budd C A | Engines |
| CA978377A (en) * | 1971-12-17 | 1975-11-25 | Engelhard Minerals And Chemicals Corporation | Process for combusting carbonaceous fuel |
| GB1471494A (en) * | 1974-05-29 | 1977-04-27 | Ver Flugtechnische Werke | Arrangement for starting an aircraft-engine and for driving aircraft auxiliary equipment |
| GB2011091B (en) * | 1977-12-22 | 1982-04-28 | Gen Electric | Method and apparatus for calculating turbine inlet temperature |
| US6931833B2 (en) * | 2003-04-30 | 2005-08-23 | United Technologies Corporation | Pulse combustion device |
-
2005
- 2005-12-26 CN CNB2005101325618A patent/CN100365256C/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033248A (en) * | 2014-06-04 | 2014-09-10 | 华能国际电力股份有限公司 | Ground gas turbine utilizing pulse detonation combustion |
| CN104033248B (en) * | 2014-06-04 | 2015-10-07 | 华能国际电力股份有限公司 | Ground gas turbine utilizing pulse detonation combustion |
| CN113048512A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Fuel grading control assembly, fuel system, gas turbine, override valve and fuel grading control method |
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| Publication number | Publication date |
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| CN100365256C (en) | 2008-01-30 |
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Granted publication date: 20080130 Termination date: 20100126 |