CN102654079A - Technical scheme of intermittent inflating turbine engine - Google Patents
Technical scheme of intermittent inflating turbine engine Download PDFInfo
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- CN102654079A CN102654079A CN2012101151033A CN201210115103A CN102654079A CN 102654079 A CN102654079 A CN 102654079A CN 2012101151033 A CN2012101151033 A CN 2012101151033A CN 201210115103 A CN201210115103 A CN 201210115103A CN 102654079 A CN102654079 A CN 102654079A
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Abstract
The invention provides a technical scheme of an intermittent inflating turbine engine. The type of engine mainly comprises a ring-body-shaped combustion chamber stator, a front functional end cover (rotor) and a rear functional end cover (rotor), wherein the ring-body-shaped combustion chamber stator is formed by a plurality of integral combustion chambers which are arranged into a ring and are same in shape and dimension, and the two functional end covers (rotors) rotate synchronously. During the operation process, when the front and rear parts of the combustion chamber are open, the combustion chamber is pressurized and ventilated, when oil mixing and ignition are carried out in the combustion chambers, the front end of the combustion chamber is sealed by the front end cover, thus a turbine blade behind the combustion chamber is pushed to rotate and do wok by utilizing high-pressure fuel gas efficiently; from the point of view of the whole engine, the engine pushes the turbine blade to rotate and do work by utilizing the high-pressure fuel gas continuously; from the point of view of certain combustion chamber, the combustion chamber has the characteristic of intermittent and cycle operation; the technical scheme of the intermittent inflating turbine engine is suitable for all occasions with easy flowing fuel materials which are combusted by virtue of air, and is widely applied to all mechanical motive power devices, is simple in structure, is low in operating temperature of the engine body, is short in engine body, is light in weight, is high in fuel oil power efficiency, and obtains high bypass ratio and thrust-weight ratio.
Description
Affiliated technical field
The present invention provides a kind of novel intermittent qi of chong channel ascending adversely turbogenerator technological scheme; This h type engine h is mainly by some annular array, the firing chamber stator that shape, the entire body firing chamber that size is identical form and forward and backward two function end cap compositions such as (rotors) that rotate synchronously.In the engine working process; When before and after the firing chamber, all being in open state the punching press ventilation is carried out in the firing chamber; When will be in the firing chamber contaminated product during with igniting, front cover seals the front end of firing chamber, thereby efficiently utilizes high-pressure gas to promote turbine blade rotation acting behind the firing chamber.This invention motor is fit to the occasion that all interdependent air burnings are prone to flowing fuel, is widely used in all kinds of mechanical driver units, like various air equipments etc.
Background technique
Motor is the heart of power equipment, directly influences the operation conditions of power equipment.At present, in the society open and extensive use mainly contain two types with the technological relevant motor of the present invention, the one, reciprocating engine, the one, gas turbine engine.
Reciprocating engine: such motor mainly is made up of firing chamber and piston etc., comprises mainly in the acting process that air-breathing, contaminated product, igniting, burning produce high-pressure gas and promote piston acting several stages.The reciprocating engine structure is complicated, and suction port, air outlet are very little, and power is comparatively limited, and phenomenons such as carbon distribution obstruction take place easily.Such power plant are the motor vehicle extensive use.
Gas turbine engine: such motor has a lot of subclasses; All mainly form by low pressure and high-pressure compressor, firing chamber and gas turbine; With regard to the firing chamber; Its co-operation characteristics be calm the anger continuously, oil spout, burning, utilize burning to produce the blade rotation acting of high-pressure gas propelling gas turbine engine.Main power plant as powerful device are like aeroengine etc.Because firing chamber and turbine all are in the hot operation state for a long time; But also bear gas turbine when starting and shutdown; The thermal shock that causes because of the temperature acute variation; Operating conditions is abominable, so they are the critical components in decision gas turbine life-span, member must be that structural strength height and resistant to elevated temperatures material are processed.Secondly, the gas turbine engine outlet temperature is very high, and utilization efficiency of heat energy is low; For making combustion gas be one-way flow, must keep constantly being pressed into high-pressure air to the firing chamber, there is the pressure loss phenomenon, engine structure is still relatively complicated, and fuselage is long, and weight is big, seriously restricts the bypass ratio and the thrust weight ratio of motor.
Summary of the invention
Qi of chong channel ascending adversely at the intermittence turbogenerator that technology of the present invention relates to; Mainly comprise one by some annular array; The ring body shape stator (2) that shape, the identical entire body firing chamber of size constitute, one have the front cover (5) to firing chamber ram-air and sealing function in the stator, a rear end cover (6) that has to row's ventilation of stator firing chamber and acting function, and prime calm the anger fan (7,8), rotating shaft (4), engine housing (1) and fuel supply, ignition system etc.Wherein:
The medial and lateral of ring body shape stator (2) generally can be provided with some bar shaped radiating fin or heat sink strip (2-4,2-5).
The chamber front end cover plate is provided with air inlet window (5-2), and can before the front end cover plate, set up the one-level fan (5-3) of calming the anger.
On the rear end cover of firing chamber or for being designed with the window of giving vent to anger (6-2a, 6-2b); And the semi open model turbine rotor that blade (6-3) that one or more acting turbine blade and the airway dysfunction that changes gear should be arranged is formed is set at the window place of giving vent to anger, or directly be designed to the turbine rotor that standard-sized sheet is put state.
Front cover (5) and rear end cover (6) are close to former and later two end faces of firing chamber stator (2) respectively, and forward and backward end cap is fixed tightly in together through the rotating shaft (4) at stator (2) center through the firing chamber with the fan (7,8) of calming the anger jointly, keeps rotating synchronously.
Work characteristics: in engine working process; When being in open state before and after the firing chamber, the punching press ventilation is carried out in the firing chamber; When will be in the firing chamber during contaminated product igniting; Seal by the front end of front cover, thereby efficiently utilize high-pressure gas to promote turbine blade rotation acting behind the firing chamber the firing chamber.Therefore, study carefully whole motor, it utilizes high-pressure gas to promote turbine blade rotation acting continuously, has and the identical mode of work-doing of gas turbine engine in the past; But study carefully certain firing chamber, it be intermittently, periodic duty, thereby have the similar work characteristics of reciprocating engine again, this motor of the present invention just and the visibly different place of turbogenerator in the past.
According to above work characteristics, in engine working process, with regard to certain firing chamber, the most basic corresponding relation () of forward and backward two end caps and firing chamber working state is:
(1) opens---opening---punching press ventilation;
(2) sealing---opening---contaminated product, ignition-powering.
When being taken at the most basic corresponding relation () situation, rear end cover is actual to be the turbine rotor that a standard-sized sheet is put state.
For adapting to high-power situation, corresponding relation (two) and (three) that forward and backward two end caps and firing chamber working state are more perfect.
Corresponding relation (two):
(1) opens---opening---punching press ventilation;
(2) open---sealing---punching press pneumatosis;
(3) sealing---opening---contaminated product, ignition-powering.
Corresponding relation (three):
(1) opens---opening---punching press ventilation;
(2) open---sealing---punching press pneumatosis;
(3) sealing---sealing---contaminated product;
(4) sealing---opening---ignition-powering.
Above corresponding relation (two), (three) corresponding relation () have relatively increased punching press pneumatosis link (2), and purpose is to make that enough fuel can fully burn in the firing chamber, improves engine power; And corresponding relation (three) relatively corresponding relation (), (two) then will supply contaminated product and ignition-powering to be divided into two, make the firing chamber outside in fuel can burn in the moment completion, with the abundant raising fuel effect of doing work.
In order to adapt to various particular design technical requirementss; Also can design other corresponding relation; And set up other function facility and take other effective measures; As set up multistage force(d) (draft) fan, adjacent force(d) (draft) fan is taked the clockwise and anticlockwise measure, and locates to set up the afterbunring air jet system and establish the one-level standard-sized sheet again at afterbody to put turbine etc. in rear end cover axle center backward.
No matter increase which kind of other function facility, but in the forward and backward two function end caps and firing chamber working state that the present invention relates to, always exist standard-sized sheet to put the punching press ventilation of state and two links the most basic of sealing and open state work by combustion, that is:
(1) opens---opening---punching press ventilation;
(2) sealing---opening---ignition-powering.
Make the front cover sealed width greater than the give vent to anger width of window of rear end cover acting in order fully to improve the effect that high-pressure gas promotes the turbine blade acting, can to design, promptly prolong the effect time.
In sum, the excellent characteristics of qi of chong channel ascending adversely turbogenerator of the present invention:
(1) contrast internal combustion piston engine, it has simple in structure, is difficult for the carbon distribution blocking phenomenon takes place, and the power allowed band is big, and Applicable scope is more extensive.
(2) contrast other gas turbine engine, exempted the high pressure device of calming the anger, have advantage of simple structure; Owing to take the circular gap mode of work-doing; The average operating temperature in firing chamber is obviously reduced; Though the continuous operation of acting turbine blade owing to limited between the high-temperature zone, is convenient to take effective cooling measure in hot environment very much; Thereby reduce the technical requirements of motor manufactured materials resistance to high temperature, make the longer service life of motor; When the combustion chambers burn ignition-powering, because chamber front end is sealed by front cover, the pressure loss phenomenon can not take place, improved the fuel oil effect; The engine export temperature is very low, and utilization efficiency of heat energy obviously improves.
As with technical application of the present invention to jet airplane, adopt multistage force(d) (draft) fan, and be pressed into gas and be divided into axial flow (a), by-pass flow (b) and be depressed into firing chamber three parts such as (c), its axial flow, by-pass flow have the effect of cooling combustion chamber stator (2) simultaneously.This type turbojet architecture is simple, the fuselage operating temperature is lower, fuselage short, in light weight, fuel oil effect height, obtains higher bypass ratio and thrust weight ratio.
Description of drawings
Accompanying drawing 1: be qi of chong channel ascending adversely at intermittence turbogenerator firing chamber stator center cross-sectional structure schematic representation.
Accompanying drawing 2: for qi of chong channel ascending adversely at intermittence turbogenerator along the longitudinal cross-section, axle center structural representation.
Shown in the accompanying drawing 2, intermittently the qi of chong channel ascending adversely turbogenerator mainly is made up of ring body shape firing chamber stator (2), chamber front end lid (driven rotor) (5), firing chamber rear end cover (initiatively turbine rotor) (6), prime force(d) (draft) fan (7,8), engine housing (1), central rotating shaft (4), supporting part (11), front and rear cover positioning element and oil supply and ignition system.
Accompanying drawing 3: be front-view schematic diagram according to a kind of qi of chong channel ascending adversely at intermittence turbogenerator front and back ends cover plate structure of corresponding relation (two) design.Wherein, accompanying drawing 3-a is the front-view schematic diagram of front end cover plate, and accompanying drawing 3-b is the front-view schematic diagram of rear-end plate.
Take unified mode that each parts is numbered in the accompanying drawing, existing each parts brief description of intermittently qi of chong channel ascending adversely turbogenerator is following:
Ring body shape firing chamber stator (2): mainly be made up of outer cylinder (2-1), inner cylinder (2-2) and firing chamber dividing plate (2-3), it is one of critical component of motor of the present invention.Accompanying drawing 1, design the firing chamber of 16 annular array shown in 3 altogether.Ring body shape firing chamber stator relies on its outrigger (2-6) and engine housing (1) to be fixed together.For making ring body shape firing chamber stator keep the lower temperature state, bar shaped radiating fin or heat sink strip (2-4,2-5) are set respectively in the medial and lateral of annulated column bodily form firing chamber usually.
Engine chamber front cover (driven rotor) (5): it is the key and the core component of other turbogenerator of motor difference of the present invention.Front cover (5) mainly is made up of sealing panel part (5-1), air inlet window (5-2) and other function auxiliary, is fixed together with central rotating shaft (4) through center piece (5-7), the metal tip (9-3).
For realizing better firing chamber punching press ventilation, 2 in accompanying drawing is shown in and has set up one-level calm the anger fan (5-3) and inside and outside gas collection cylinder (5-8,5-9) before the air intake window mouth.The high efficiency of the harmonious and work that the design considered of the fan blade of calming the anger (5-3) is inhaled, calmed the anger.
As invent technical application to aero-jet engine; Or for making the engine combustion indoor side and the outside keep the lower temperature state; Usually evenly offer in front cover (5) inboard and somely paraxially flow to transom window mouth (5-4), and set up paraxial stream blade (5-6) and the by-pass flow blade (5-5) of calming the anger of calming the anger.
Engine chamber rear end cover (initiatively turbine rotor) (6): it is one of critical component of motor of the present invention.Shown in accompanying drawing 3-b, for designing the rear-end plate of aforementioned corresponding relation (two) situation, it is actual to be the turbine rotor of a semi-open state.Rear end cover mainly is made up of sealing panel part (6-1), window of giving vent to anger (6-2a, 6-2b) and turbine blade (6-3), is fixed together with central rotating shaft (4) through center piece (6-7), the metal tip (9-4).The always corresponding firing chamber that is in the ignition state of the window (6-2a) of wherein giving vent to anger, the turbine blade (6-3) that is provided with thereafter is to be produced the blade that high-temperature high-pressure fuel gas promotes acting, employed its resistance to high temperature of material considered by burning; The always corresponding firing chamber that is in row's ventilation state of the window (6-2b) of giving vent to anger, the turbine blade that is provided with thereafter is the blade that plays firing chamber row's gas exchange action.
Like accompanying drawing 2, shown in 3, be to increase the torque and acting effect of rear end cover power rotor, can with the window of giving vent to anger (6-2a) inner edge outward lateral deviation move, and spread too early with inside and outside arc surface (6-8,6-9) confined jet high-pressure gas.
As invent technical application to aero-jet engine; Or for making the engine combustion indoor side and the outside keep the lower temperature state; Usually evenly offer some paraxial effluent gases windows (6-4) in the rear end cover inboard, and set up paraxial stream exhaust vane (6-6) and by-pass flow suction and discharge blade (6-5).
Prime supercharging air fan: shown in the accompanying drawing 2, designed the two-stage supercharging fan before the front cover, i.e. force(d) (draft) fan (7) and (8).The progression of prime force(d) (draft) fan should be decided according to concrete needs.
Rotating shaft and supporting part: motor shown in the accompanying drawing 2 designs a special stand foremost, by support (11-1), carriage center part (11-2) with start anterior tip to divide fan housing (12) to form; Next has set up inner support (2-7) in burning stator inboard and a little inner cylinder (2-8) is used as another support.Through bearing (3-1) and (3-2), two fulcrums of stationary engine central rotating shaft (4) respectively.All rotatable parts of motor are all fixed with rotating shaft (4) or are linked together, and realize interlock with rotating shaft (4).
Require the central lines of rotating shaft (4) center line and ring body shape firing chamber (stator) (2), and vertical each other with the front and rear end of ring body shape firing chamber (stator).
Parts are regulated in forward and backward end cap location, firing chamber: shown in the accompanying drawing 2, mainly be made up of the nut (13-1,13-2) at powerful stage clip (15), metallic shim (14), metal sleeve (10-1,10-2,10-3,10-4) and central rotating shaft (4) two ends etc.Turnover through adjusting nut (13-1,13-2) realizes transferring the distance between forward and backward end cap in firing chamber and front and rear end, firing chamber.Also can adopt alternate manner to realize forward and backward end cap location, firing chamber is regulated.
Embodiment
1, firing chamber stator (2) is an engine technology core of the present invention with the design of the forward and backward end cap in firing chamber (5,6).Must guarantee in the design process that the firing chamber possesses the characteristics of intermittent cyclic punching press ventilation and ignition-powering, promptly guarantee must possess two corresponding relations the most basic in forward and backward two function end caps and the firing chamber working state:
(1) opens---opening---punching press ventilation;
(2) sealing---opening---ignition-powering.
The design procedure of the forward and backward end cap of firing chamber stator and firing chamber:
(1) at first considers the application start, confirm the output power and the corresponding relation of confirming to work in suitable forward and backward end cap and firing chamber of motor, obtain operation cycle T.
T=kt formula (1)
In the formula (1), t be on the end cap certain o'clock through the time of a firing chamber, k by an operation cycle middle-end cover a bit the burning number of chambers of process, be predefined engine operating duration constant, be integer or non-integer, general value 2.0～5.0.
When selecting k to be 2.0, can only be the aforementioned mode of operation of corresponding relation () the most basically.
In order to give full play to the effect of high-pressure gas acting, can take to strengthen the way of front cover sealed width, this practical function is exactly the effect time that prolongs high-pressure gas.
(2) confirm tentatively to decide the engine geometry size according to the output power size, and the operating time constant k of synthetic setting is confirmed the burning number of chambers N on the stator of firing chamber.Burning number of chambers N on the stator of firing chamber is an integer, and is the integer multiple n that sets the operating time constant k.That is:
N=kn formula (2)
In the formula (2), n is actual to be exactly the firing chamber number that work by combustion takes place in the stator of designed combustion chamber all the time.
(3) according to mode of operation, the operating time constant k of engine chamber stator dimensions size, burning number of chambers N and setting, the form of the forward and backward end cap in firing chamber that design is corresponding mainly is to confirm turnover gas position of window and width.
2, engine chamber rear end cover (initiatively turbine rotor) (6): one of critical component that it is a structure in the motor of the present invention, change of form is bigger; Its form is relevant with the designed engines mode of operation, promptly is decided by the corresponding relation situation of predefined forward and backward end cap and firing chamber working state.
As 1: when being designed to the most basic aforementioned corresponding relation (), rear end cover mainly is made up of turbine blade (6-3), is fixed together with central rotating shaft (4) through center piece (6-7), the metal tip (9-4).Actual is exactly the turbine rotor that a standard-sized sheet is put state; But work characteristics because of motor of the present invention; The turbine upper blade is different according to the present position; The effect of being played has two kinds, and a kind of is the blade that is produced high-temperature high-pressure fuel gas promotion acting for a long time by burning, and a kind of is the blade that plays for a long time firing chamber row's gas exchange action.The former employed its resistance to high temperature of material considered.
As 2: when being designed to aforementioned corresponding relation (two), when description of drawings, explained.
As 3: when being designed to aforementioned corresponding relation (three), rear end cover is similar shown in rear end cover and the accompanying drawing 3, also is the turbine rotor of a semi-open state; But because oil spout is not carried out with igniting simultaneously; And in the injection process, the forward and backward end cap of firing chamber all is in sealing state, if this moment, the firing chamber was in the condition of high temperature; Or design and manufacture view exist defective that the fiery phenomenon of string takes place; Can cause the firing chamber to burn in advance and blast or motor damage that when therefore selecting this mode of operation for use, each item technical requirements such as its design, manufacturing are higher.
3, typical implementation case study:
Qi of chong channel ascending adversely at the intermittence turbogenerator of accompanying drawing 1,2, design shown in 3, the burning number of chambers N of firing chamber stator is 16, adopts the actual corresponding relation of forward and backward end cap and firing chamber working state following:
(1) open---sealing---punching press pneumatosis, the time is 0.5t;
(2) sealing---sealing---ready wait, the time is t;
(3) sealing---opening---contaminated product, ignition-powering, the time is 1.5t;
(4) open---opening---punching press ventilation, the time is t.
Show that more than it is 4t that a needed time of light-off period is accomplished in each firing chamber, i.e. operating time constant k=4.0 of design; All the time, to be in the burning number of chambers n of work by combustion state be 4 to this motor.
4, for simplifying engine oil program of the present invention; Can be by the fuel feeding of center foremost of rotating shaft (4); And take rotating shaft (4) leading portion is processed modes such as the hollow tubular axis of heavy wall, draw to chamber front end lid place, and branch to each oil nozzle of being installed on the front end cover plate (A1 of accompanying drawing 3～A4); Oil nozzle rotates with front cover (5) like this, can avoid the use of some complicated fuel feeding detections, control circuit.(A1～A4) considered can realize the place of best contaminated product effect, and requires oil nozzle place and chamber front end capping to keep smooth, and the phenomenon of protrusion can not be arranged in design oil nozzle position.
For make the fuel that sprays into the firing chamber can more evenly mix with the air in the firing chamber with fuel in the lubricant oil that adds can effectively arrive on the end cap face that contacts; Can consider that the place ahead corresponding with oil nozzle in the firing chamber sets up function smallclothes, play the effect that makes oil spout that reflection or scattering take place.
5, for simplifying engine ignition program of the present invention; Can spark plug be installed near first turbine blade of the window of respectively giving vent to anger (6-2a) of rear end cover (6); Harness causes rotating shaft (4) through supporting element and locates; Near rotating shaft (4), cause spark plug again, spark plug rotates with rear end cover like this, can avoid the use of some complicated igniting detection, control circuits; Because firing chamber of the present invention circular array; If the block board thickness between the firing chamber is less than the give vent to anger width of window (6-2a) of firing chamber rear end cover; Give vent to anger window (6-2a) when crossing over next firing chamber of entering, a firing chamber when rear end cover, can realize the automatic ignition operation of next firing chamber immediately.But in order to make the engine ignition success rate reach 100%, can be provided with high temperature resistant, anti-oxidant and can be at the give vent to anger spark plug place of window (6-2a) of rear end cover, or keep spark plug to work incessantly from the heat accumulation metalwork or the alloy components of vehementization.
6, by preceding said, the most of component that constitute motor of the present invention all belong to the circle symmetry and have balanced parts.In manufacture process, especially must be noted that control the run up circular symmetry and the harmony of parts, keep center of gravity in rotating shaft in the heart.Can adopt each critical piece of casting process production motor of the present invention.
7, direct fixation can be taked in the location of forward and backward end cap, adopts this method to do accurate design, to make associated components; Secondly; Shown in accompanying drawing 2, can utilize powerful stage clip, pad (containing sleeve), screw rod or central shaft and nut etc., realize the location adjusting of forward and backward end cap through the turnover of adjusting nut; This method ratio is easier to realize, and makes things convenient for the care and maintenance of motor.
8, for make between firing chamber and forward and backward end cap infinitely near, promptly distance should infinitely be tending towards+0mm between surface of contact, requires each surface of contact all to want ten minutes smooth, and strict vertical engine shaft axis; Secondly; Some aperture and grooves can be set in the appropriate location on the stator of firing chamber; Support is down through firing chamber top to let lubricant oil; Former and later two that directly are filled into the firing chamber automatically along aperture and groove contact on the end face, or in fuel, add an amount of machine oil etc., to reduce the pivoting friction resistance of forward and backward end cap.
Claims (10)
1. the present invention provides a kind of qi of chong channel ascending adversely at intermittence turbogenerator technological scheme; Qi of chong channel ascending adversely at the intermittence turbogenerator that technology of the present invention relates to is a kind of mainly by some annular array, and two forward and backward function end cap compositions such as (rotors) that rotate synchronously of firing chamber are close in ring body shape firing chamber stator that shape, the entire body firing chamber that size is identical form and maintenance.
2. the present invention's qi of chong channel ascending adversely at intermittence turbogenerator has multiple mode of operation; But in the course of the work; Always possess two the most basic operating conditions or working links: when all being in open state before and after the firing chamber, the punching press ventilation is carried out in the firing chamber, promptly forward and backward two function end caps all are in open state; When will be in the firing chamber contaminated product during with igniting, seal by the front end of front cover, thereby efficiently utilize high-pressure gas to promote turbine blade rotation acting behind the firing chamber the firing chamber, promptly forward and backward two function end caps then are in sealing and open state respectively.
3. the present invention's qi of chong channel ascending adversely at intermittence turbogenerator ring body shape firing chamber stator is one of critical component of intermittently qi of chong channel ascending adversely turbogenerator; It mainly is made up of outer cylinder, inner cylinder, firing chamber dividing plate and other function auxiliary, and the function auxiliary comprises inboard and outrigger, inboard and the outside bar shaped radiating fin or the heat sink strip of ring body shape firing chamber.
4. the present invention's qi of chong channel ascending adversely at intermittence turbogenerator chamber front end function lid (driven rotor) is the key and the core component of other turbogenerator of motor difference of the present invention; It mainly is made up of combustion chamber sealing faceplate part, firing chamber air inlet window and other function auxiliary; The function auxiliary comprises calm the anger fan and the inside and outside gas collection cylinder of setting up before the firing chamber air inlet window, and paraxial transom window mouth and paraxial stream blade, the by-pass flow blade of calming the anger of calming the anger that flows to.
5. the present invention's qi of chong channel ascending adversely at intermittence turbogenerator firing chamber back-end function lid (initiatively turbine rotor) is one of critical component of motor of the present invention; Its form is relevant with predefined engine working mode; The corresponding relation situation that promptly is decided by predefined forward and backward end cap and firing chamber working state; It can be the active turbine rotor that a standard-sized sheet is put, also can be one with the corresponding semi-open state active turbine rotor of front-end functionality lid with sealing panel part, exhaust window, exhaust blade and acting turbine blade.
6. for simplifying intermittently qi of chong channel ascending adversely turbogenerator fuel feeding program of the present invention; Can be by the fuel feeding of center foremost of rotating shaft; And take the rotating shaft leading portion is processed modes such as the hollow tubular axis of heavy wall, draw to chamber front end lid place, and branch to each oil nozzle that is installed on the front end cover plate; Oil nozzle rotates with front cover, promptly can avoid the use of some complicated fuel feeding detections, control circuit.
7. for simplifying intermittently qi of chong channel ascending adversely turbogenerator ignition procedure of the present invention; Can spark plug be installed near window first turbine blade of giving vent to anger of rear end cover; Harness causes rotating shaft place through supporting element; Be connected to each spark plug along rotating shaft again, spark plug rotates with rear end cover like this, can avoid the use of some complicated igniting detection, control circuits.
8. in order to make the present invention's qi of chong channel ascending adversely at intermittence turbogenerator ignition success rate reach 100%, heat accumulation metalwork or alloy components high temperature resistant, anti-oxidant and that can turn white-hot can be set at the spark plug place.
9. for reducing the intermittently pivoting friction resistance of the forward and backward end cap of qi of chong channel ascending adversely turbogenerator of the present invention; Some aperture and grooves can be set in the appropriate location on the stator of firing chamber; Let lubricating oil through firing chamber top support down, former and later two that are filled into the firing chamber automatically along aperture and groove contact on the end face.
10. for making the present invention's qi of chong channel ascending adversely at intermittence turbogenerator maintain easily and maintain, can utilize powerful stage clip, pad (containing sleeve), screw rod or central shaft and nut etc., realize the location adjusting of the forward and backward end cap in firing chamber through the turnover of adjusting nut.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012101151033A CN102654079A (en) | 2012-04-18 | 2012-04-18 | Technical scheme of intermittent inflating turbine engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012101151033A CN102654079A (en) | 2012-04-18 | 2012-04-18 | Technical scheme of intermittent inflating turbine engine |
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| CN102654079A true CN102654079A (en) | 2012-09-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106662330A (en) * | 2014-08-20 | 2017-05-10 | 赛峰航空器发动机 | Connection device comprising several curved concentric tubes |
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2012
- 2012-04-18 CN CN2012101151033A patent/CN102654079A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106662330A (en) * | 2014-08-20 | 2017-05-10 | 赛峰航空器发动机 | Connection device comprising several curved concentric tubes |
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Application publication date: 20120905 |