CN100365256C - Pulsating flow gas turbine - Google Patents
Pulsating flow gas turbine Download PDFInfo
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- CN100365256C CN100365256C CNB2005101325618A CN200510132561A CN100365256C CN 100365256 C CN100365256 C CN 100365256C CN B2005101325618 A CNB2005101325618 A CN B2005101325618A CN 200510132561 A CN200510132561 A CN 200510132561A CN 100365256 C CN100365256 C CN 100365256C
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- firing chamber
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Abstract
The present invention relates to a pulsating flow gas turbine which comprises a crankshaft, a compressor set, a turbine set and a combustion chamber connected between the compressor set and the turbine set, wherein the compressor unit and the turbine set share the crankshaft. A gas gate is arranged at an inlet of the combustion chamber, an oil injection nozzle and an ignition device are arranged on the wall of the combustion chamber, wherein the gas gate, the oil injection nozzle and the ignition device are controlled by a microprocessor controller to circularly work according to numerical time, and input signals of the microprocessor controller are taken from a rotation number sensor arranged on the crankshaft. The present invention is provided with double combustion chambers connected in parallel, an independent work turbine shaft and an independent work turbine set as a preferred plan. The pulsating flow gas turbine can increase the combustion temperature, outputs the working pressure of turbines, increases low-speed performance and output efficiency, saves materials, is favorable for the combustion chambers and the turbines to be cooled down and is easy to start, and moreover, the application of a dual-shaft scheme further improves low rotation number performance.
Description
Technical field
The present invention relates to a kind of gas turbine, particularly a kind of pulsating flow gas turbine.
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, one arbor is arranged, the calm the anger unit and the turbines of shared this arbor, and be connected described at least two firing chambers of calming the anger between unit relief opening and the described turbines suction port, suction port place in each firing chamber, valve is set, oil nozzle and ignition mechanism are set on each chamber wall, each valve, oil nozzle and ignition mechanism are controlled by microprocessor controller, the input speed signal of this microprocessor is taken from the speed probe that is arranged on the described arbor, and following sequential alternation is pressed in this microprocessor control firing chamber:
A) first valve-closing;
B) the first oil nozzle oil spout;
C) first ignition device, the mixed gas burning expansion exhaust in first firing chamber;
D) first valve opening, duaspiracle cuts out;
E) the second oil nozzle oil spout;
F) second ignition device, the mixed gas burning expansion exhaust in second firing chamber;
G) duaspiracle is opened.
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 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.
Pulsating flow gas turbine of the present invention can be realized hybrid burning, improves 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 pulsating flow gas turbine of the present invention double combustion chamber single shaft schematic representation;
Fig. 4 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, do more detailed explanation below in conjunction with embodiment.
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, it still was unavoidable that front end leaks.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.
Embodiment 1:
The pulsating flow gas turbine of present embodiment has the firing chamber of two parallel connections, concrete visible Fig. 4.This figure is depicted as the schematic representation of 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.
The suction port of firing chamber 5,6 is connected in parallel on the relief opening 20 of the unit 1 of calming the anger, relief opening is connected in parallel on the suction port of turbines 2, and two firing chambers are provided with independently valve 7,8, oil nozzle 9,10 and ignition mechanism 18,19, 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 use mechanical type control mode more complicated, control accuracy deficiency, realize difficulty, simultaneously in working control, also need to gather the moment of torsion of output shaft, the pressure of firing chamber or the like data, 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 2:
Fig. 5 is the schematic representation of present embodiment, 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 slow-speed of revolution moment of torsion.
Claims (4)
1. pulsating flow gas turbine, comprise arbor (16), unit of calming the anger (1) of shared this arbor (16) and turbines (2), it is characterized in that at least two firing chambers of parallel connection (5 between the suction port (14) of the relief opening (20) of the described unit of calming the anger (1) and described turbines (2), 6), in each firing chamber (5,6) suction port place, independently valve (7 is set, 8), in each firing chamber (5,6) independently oil nozzle (9 is set on the wall, 10) and ignition mechanism (18,19), described valve (7,8), oil nozzle (9,10) and ignition mechanism (18,19) control by microprocessor controller, the input speed signal of this microprocessor is taken from the speed probe (15) that is arranged on the described arbor, and following sequential alternation is pressed in this microprocessor control firing chamber:
A) first valve (7) is closed;
B) first oil nozzle (9) oil spout;
C) first ignition mechanism (18) igniting, the mixed gas burning expansion exhaust in first firing chamber (5);
D) first valve (7) is opened, and duaspiracle (8) cuts out;
E) second oil nozzle (10) oil spout;
F) second ignition mechanism (19) igniting, the mixed gas burning expansion exhaust in second firing chamber (6);
G) duaspiracle (8) is opened.
2. pulsating flow gas turbine according to claim 1 is characterized in that arbor (16) connection reducer (4), exports through reducer output shaft (13).
3. pulsating flow gas turbine according to claim 1, 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).
4. pulsating flow gas turbine according to claim 3 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 CN1789686A (en) | 2006-06-21 |
| CN100365256C true CN100365256C (en) | 2008-01-30 |
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| 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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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113048512B (en) * | 2019-12-27 | 2022-08-16 | 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 |
Citations (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 |
| GB1420968A (en) * | 1971-12-17 | 1976-01-14 | Engelhard Min & Chem | Method for oxidising 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 |
| GB2011091A (en) * | 1977-12-22 | 1979-07-04 | 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
Patent Citations (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 |
| GB1420968A (en) * | 1971-12-17 | 1976-01-14 | Engelhard Min & Chem | Method for oxidising 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 |
| GB2011091A (en) * | 1977-12-22 | 1979-07-04 | Gen Electric | Method and apparatus for calculating turbine inlet temperature |
| US6931833B2 (en) * | 2003-04-30 | 2005-08-23 | United Technologies Corporation | Pulse combustion device |
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| Publication number | Publication date |
|---|---|
| CN1789686A (en) | 2006-06-21 |
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Granted publication date: 20080130 Termination date: 20100126 |