CN105697148B - Turbogenerator - Google Patents
Turbogenerator Download PDFInfo
- Publication number
- CN105697148B CN105697148B CN201610222428.XA CN201610222428A CN105697148B CN 105697148 B CN105697148 B CN 105697148B CN 201610222428 A CN201610222428 A CN 201610222428A CN 105697148 B CN105697148 B CN 105697148B
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- Prior art keywords
- casing
- turbogenerator
- combustion chamber
- gas
- combustion
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
The invention provides a kind of turbogenerator, and it includes：Casing, turbine, flow splitter, housing, oil circuit component and igniter.Flow splitter is connected to the front end of casing and turbine is sheathed on together with casing.Housing houses casing, and forms outer culvert combustion chamber with the outside wall surface of casing, and flow splitter and casing are internally formed intension gas channel.Oil circuit component is controlled to be communicated in outer culvert combustion chamber.Igniter is arranged in outer culvert combustion chamber, for being lighted a fire to combustion gas, and then combustion gas detonating combustion.In the turbogenerator of the present invention, the structure of outer culvert combustion chamber is simple, in light weight, substantially increases the thrust-weight ratio of engine.It is arranged at based on igniter in outer culvert combustion chamber, the combustion gas rotation detonating combustion in outer culvert combustion chamber can be made to enter, so as to which the turbine engine combustion for solving the problems, such as traditional is unstable, the thermal efficiency of burning is improved, and improves the fuel economy and functional reliability of turbogenerator.
Description
Technical field
The present invention relates to aviation power technical field, more particularly to a kind of turbogenerator.
Background technology
At present, high thrust-weight ratio is still the important performance indexes that aero gas turbine engine is pursued, and improves the way of thrust-weight ratio
Footpath mainly has two：First, mitigate weight；Second, increase thrust.For first point, in existing material and technological level condition
Under, it is proof strength and life requirements, loss of weight space is extremely limited.For second point, realization means mainly have increase flow and
It is horizontal to increase engine temperature rise.Because import sectional dimension is restricted by aircraft, flow can not arbitrarily increase, therefore,
In a short time, increasing thrust can only be from the point of view of increase engine temperature rise ratio.For routine turbofan,
The heat release amount of main chamber suffers from the limitation of turbine material, it is difficult to further improve, and by-pass air duct air-flow is without turbine
Part, thus, higher level can be reached to its temperature.The existing scheme that conventional deflagration combustion chamber is set in by-pass air duct at present,
Yet with by-pass air duct narrow space, there is certain difficulty in arrangement conventional combustion cell structure, meanwhile, present in conventional combustion room
The problems such as thermal efficiency is low, combustion instability, high pollutant emission level still has.
The content of the invention
In view of problem present in background technology, it is an object of the present invention to provide a kind of turbogenerator, outside it
It is simple to contain the structure of combustion chamber, it is in light weight, substantially increase the thrust-weight ratio of engine.
It is another object of the present invention to provide a kind of turbogenerator, which solves traditional turbine engine combustion
The problem of unstable, the thermal efficiency of burning is improved, improve the fuel economy and functional reliability of engine.
To achieve these goals, the invention provides a kind of turbogenerator, it includes：Casing, turbine, shunting
Ring, housing, oil circuit component and igniter.Turbine is contained in casing.Flow splitter be connected to the front end of casing and with casing one
Rise and be sheathed on turbine.Housing houses casing and forms outer culvert combustion chamber with the outside wall surface of casing, and flow splitter and casing is interior
Portion forms intension gas channel.Oil circuit component is controlled to be communicated in outer culvert combustion chamber, and fuel is provided outwards to contain combustion chamber.Igniter
It is arranged in outer culvert combustion chamber, the combustion gas for being formed to entering the outer fuel contained in combustion chamber and oxygen-containing gas is carried out a little
Fire, and then combustion gas detonating combustion.
Beneficial effects of the present invention are as follows：
In the turbogenerator according to the present invention, the outside wall surface of housing and casing forms outer culvert combustion chamber, the outer culvert combustion
It is simple to burn the structure of room, it is in light weight, substantially increase the thrust-weight ratio of engine.It is arranged at based on igniter in outer culvert combustion chamber,
The combustion gas rotation detonating combustion in outer culvert combustion chamber can be made to enter, so as to which the turbine engine combustion for solving traditional is unstable
Problem, improves the thermal efficiency of burning, and improves the fuel economy and functional reliability of turbogenerator.
Brief description of the drawings
Fig. 1 is the overall structure diagram according to the turbogenerator of the present invention；
Fig. 2 is the circumferential position schematic diagram of the fuel nozzle ports on the prevapourising room in Fig. 1；
Fig. 3 is the circumferential position schematic diagram of the igniter in Fig. 1；
Fig. 4 is the enlarged diagram of the governor motion in Fig. 1.
Wherein, description of reference numerals is as follows：
The valve of 1 casing 81
The cylinder of 2 turbine 82
The cylinder body of 3 flow splitter 821
The piston rod of 4 housing 822
The gas mixer chamber of 5 oil circuit component 9
Contain combustion chamber outside 51 cartridge C
52 atomizer C1 gas accesses
6 igniter C2 gas vents
7 prevapourising room S intension gas channels
71 fuel nozzle ports F fans
8 governor motion A exhaust outlets
Embodiment
With reference to the accompanying drawings come describe in detail according to the present invention turbogenerator.
Referring to figs. 1 to Fig. 4, included according to the turbogenerator of the present invention：Casing 1, turbine 2, flow splitter 3, housing 4,
Oil circuit component 5 and igniter 6.
Turbine 2 is contained in casing 1.Flow splitter 3 is connected to the front end of casing 1 and is sheathed on turbine together with casing 1
2.Housing 4 houses casing 1, and forms outer culvert combustion chamber C with the outside wall surface of casing 1, and flow splitter 3 and casing 1 are internally formed
Intension gas channel S.Oil circuit component 5 is controlled to be communicated in outer culvert combustion chamber C, and fuel (i.e. fuel oil) is provided outwards to contain combustion chamber C.
Igniter 6 is arranged in outer culvert combustion chamber C, for entering the fuel in outer culvert combustion chamber C and the combustion of oxygen-containing gas formation
Gas is lighted a fire, and then combustion gas detonating combustion.In the turbogenerator according to the present invention, the outside wall surface shape of housing 4 and casing 1
Into outer culvert combustion chamber C, the structure of the outer culvert combustion chamber C is simple, in light weight, substantially increases the thrust-weight ratio of engine.Based on point
Firearm 6 is arranged in outer culvert combustion chamber C, can be made to enter the combustion gas rotation detonating combustion in outer culvert combustion chamber C, be passed so as to solve
The problem of turbine engine combustion of system is unstable, improves the thermal efficiency of burning, and improves the fuel oil warp of turbogenerator
Ji property and functional reliability.
According to the turbogenerator of the present invention, in one embodiment, referring to Figures 1 and 2, turbogenerator may also include：
Prevapourising room 7, it is formed between casing 1 and turbine 2, the fuel being fed to via oil circuit component 5 in prevapourising room 7 is carried out
Evaporation process.
In one embodiment, the prevapourising room 7 of reference picture 1 is by flow splitter 3, the front portion of casing 1 and the outer wall shape of turbine 2
Into.Certainly not only limit in this way, prevapourising room 7 can also be formed at other appropriate positions between casing 1 and turbine 2.
In one embodiment, referring to Figures 1 and 2, prevapourising room 7 can have：Multiple fuel nozzle ports 71, radially breakthrough form
Into the corresponding part of the casing 1 of prevapourising room 7, and along the circumferentially distributed of casing 1, each fuel nozzle ports 71 connect outer culvert combustion chamber C,
So that the fuel after evaporation process enters outer culvert combustion chamber C via each fuel nozzle ports 71.Remark additionally herein, multiple combustions
Expect that spout 71 along the circumferentially distributed of casing 1, can make fuel into outer culvert combustion chamber C direction with entering containing for outer culvert combustion chamber C
The flow direction of carrier of oxygen (as oxidant) is in 90 °, contributes to fuel fully to be blended with oxygen-containing gas.
In one embodiment, referring to Figures 1 and 2, oil circuit component 5 may include：Cartridge 51, one end is communicated in oil feeding line
(not shown), the other end are communicated in prevapourising room 7；And atomizer 52, it is arranged at and is communicated in the described another of cartridge 51
One end is simultaneously located in prevapourising room 7, and atomization process is carried out to the fuel via oil feeding line and the infeed of cartridge 51.
In one embodiment, reference picture 1, outer culvert combustion chamber C can have：Gas access C1, with the outer culvert controlled companies of combustion chamber C
It is logical and provide that oxygen-containing gas source (not shown) is controlled to be connected with outside；And gas vent C2, connected with outer culvert combustion chamber C to arrange
Contain the waste gas after being burnt in the C of combustion chamber out.Wherein, the outside oxygen-containing gas source that provides can provide purity oxygen or air.
In one embodiment, reference picture 1, turbogenerator may also include：Governor motion 8, it is arranged on outer culvert combustion chamber C's
At the C1 of gas access, to adjust gas access C1 size or close gas access C1.Wherein, the concrete operations of governor motion 8
It is as follows：When needing to increase the air mass flow for entering outer culvert combustion chamber C, gas access C1 is tuned up by controlling to adjust mechanism 8
Aperture；Correspondingly, when needing to reduce the air mass flow for entering outer culvert combustion chamber C, gas is reduced by controlling to adjust mechanism 8
Body entrance C1 aperture.
In one embodiment, reference picture 4, governor motion 8 may include：Valve 81 and cylinder 82.Valve 81, it is pivotally mounted
Position at the close gas access C1 of housing 4.Cylinder 82 may include：Cylinder body 821, one end are pivotally connected to housing 4；And
Cylinder body 821 is stretched into piston rod 822, one end, and the other end stretches out cylinder body 821 and is pivotally connected with valve 81, and cylinder 82 passes through driving
The stretching motion of 822 opposing cylinder of piston rod 821 and drive valve 81 to move pivotally to open or close gas access C1.Work as valve
81 rotate and when being gradually distance from flow splitter 3, and gas access C1 aperture becomes larger；When valve 81 rotates and moves closer to shunt
During ring 3, gas access C1 aperture tapers into；Ridden over when valve 81 turns on flow splitter 3, gas access C1 is closed.
In one embodiment, reference picture 1, turbogenerator may also include：Gas mixer chamber 9, it is formed at outer culvert combustion chamber C
Gas vent C2 corresponding between the part of housing 4 and the afterbody of casing 1, and be communicated in gas vent C2 and intension air-flow leads to
Road S.Remark additionally herein, gas mixer chamber 9 is optionally configured in turbogenerator.In some implementations
In example, gas mixer chamber 9 need not can be set in turbogenerator, the gas in intension gas channel S with outer culvert combustion chamber C
Waste gas each discharge respectively after burning.
In one embodiment, reference picture 1, turbogenerator may also include：Fan F, the axial forward end of housing 4 is arranged at,
Extraneous gas is set to be drawn into via fan F in the housing 4 of turbogenerator.Wherein, it is drawn into turbogenerator via fan F
Gas in housing 4 is partly into outer culvert combustion chamber C in the presence of flow splitter 3, and another part leads into intension air-flow
Road S.
In one embodiment, reference picture 1, turbogenerator can also have：Exhaust outlet A, after being arranged at the axial direction of housing 4
End.The gas of exhaust outlet A discharges finally can be exchanged into the thrust of turbogenerator, and then promote aircraft motion.
In one embodiment, turbogenerator may also include：Control system (not shown), it is communicatively coupled to governor motion 8
Cylinder 82, to control the motion of the piston rod 822 of cylinder 82.
Finally remark additionally, turbogenerator of the invention substitutes traditional afterbunring using outer culvert combustion chamber C
Room, reduce the total length of turbogenerator.Further, since outer combustion chamber C of containing makes outer culvert combustion using continuous rotation pinking technology
Burn room C and approximate isochoric combustion is changed into by the isobaric combustion of routine, so as to significantly improve the thermal efficiency, thus reduce turbine hair
The oil consumption rate of motivation, and then outer culvert combustion chamber C working time can be extended.
Claims (10)
1. a kind of turbogenerator, including：
Casing (1)；
Turbine (2), it is contained in casing (1)；And
Flow splitter (3), it is connected to the front end of casing (1) and turbine (2) is sheathed on together with casing (1)；
Characterized in that, turbogenerator also includes：
Housing (4), houses casing (1), and the outer culvert that the internal face of housing (4) directly forms annular with the outside wall surface of casing (1) is fired
Burn room (C), and flow splitter (3) and casing (1) are internally formed intension gas channel (S)；
Oil circuit component (5), it is controlled to be communicated in outer culvert combustion chamber (C), provide fuel outwards to contain combustion chamber (C)；And
Igniter (6), it is arranged in outer culvert combustion chamber (C), for entering the fuel and oxygenous in outer culvert combustion chamber (C)
The combustion gas that body is formed is lighted a fire, and then combustion gas detonating combustion, and detonating combustion is rotation detonating combustion.
2. turbogenerator according to claim 1, it is characterised in that turbogenerator also includes：
Prevapourising room (7), it is formed between casing (1) and turbine (2), to being fed to prevapourising room via oil circuit component (5)
(7) fuel in is evaporated processing.
3. turbogenerator according to claim 2, it is characterised in that prevapourising room (7) are by flow splitter (3), casing (1)
Front portion and the outer wall of turbine (2) formed.
4. turbogenerator according to claim 2, it is characterised in that prevapourising room (7) have：
Multiple fuel nozzle ports (71), are radially formed through the corresponding part of the casing (1) of prevapourising room (7), and along casing (1)
It is circumferentially distributed, the connection of each fuel nozzle ports (71) is outer to contain combustion chamber (C), so that the fuel after evaporation process is via each fuel nozzle ports
(71) outer culvert combustion chamber (C) is entered.
5. turbogenerator according to claim 2, it is characterised in that oil circuit component (5) includes：
Cartridge (51), one end are communicated in oil feeding line, and the other end is communicated in prevapourising room (7)；And
Atomizer (52), it is arranged at and is communicated in the other end of cartridge (51) and is located in prevapourising room (7), to warp
The fuel fed by oil feeding line and cartridge (51) carries out atomization process.
6. turbogenerator according to claim 1, it is characterised in that containing combustion chamber (C) outside has：
Gas access (C1), with outer culvert combustion chamber (C) it is controlled connect and with outside offer oxygen-containing gas source is controlled connects；And
Gas vent (C2), connected with outer culvert combustion chamber (C) to discharge the waste gas after being burnt in outer culvert combustion chamber (C).
7. turbogenerator according to claim 6, it is characterised in that turbogenerator also includes：
Governor motion (8), gas access (C1) place of outer culvert combustion chamber (C) is arranged on, to adjust gas access (C1) size
Or close gas access (C1).
8. turbogenerator according to claim 7, it is characterised in that governor motion (8) includes：
Valve (81), it is pivotally mounted to the position at close gas access (C1) place of housing (4)；And
Cylinder (82), including：
Cylinder body (821), one end are pivotally connected to housing (4)；And
Cylinder body (821) is stretched into piston rod (822), one end, and the other end stretches out cylinder body (821) and is pivotally connected with valve (81), gas
Cylinder (82) by drive piston rod (822) opposing cylinder (821) stretching motion drive valve (81) move pivotally to open or
Close gas access (C1).
9. turbogenerator according to claim 6, it is characterised in that turbogenerator also includes：
Gas mixer chamber (9), it is formed at the part of housing (4) and casing corresponding to the gas vent (C2) of outer culvert combustion chamber (C)
(1) between afterbody, and gas vent (C2) and intension gas channel (S) are communicated in.
10. turbogenerator according to claim 1, it is characterised in that turbogenerator also includes：
Fan (F), the axial forward end of housing (4) is arranged at, extraneous gas is drawn into the shell of turbogenerator via fan (F)
In body (4)；
Turbogenerator also has：
Exhaust outlet (A), it is arranged at the axial rearward end of housing (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222428.XA CN105697148B (en) | 2016-04-11 | 2016-04-11 | Turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610222428.XA CN105697148B (en) | 2016-04-11 | 2016-04-11 | Turbogenerator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105697148A CN105697148A (en) | 2016-06-22 |
| CN105697148B true CN105697148B (en) | 2018-04-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610222428.XA Active CN105697148B (en) | 2016-04-11 | 2016-04-11 | Turbogenerator |
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| Country | Link |
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| CN (1) | CN105697148B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107100735B (en) * | 2017-06-27 | 2018-11-20 | 哈尔滨工程大学 | A kind of marine gas turbine based on combined type combustion chamber |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19600824A1 (en) * | 1995-09-28 | 1997-07-17 | Gerhard Ittner | Turbine shaft load drive mechanism for hypersonic region |
| EP1532358A2 (en) * | 2002-06-26 | 2005-05-25 | R-Jet Engineering Ltd. | Orbiting combustion nozzle engine |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN103835836A (en) * | 2014-03-10 | 2014-06-04 | 金剑 | Bypass-ratio controllable gas turbine |
| CN205592026U (en) * | 2016-04-11 | 2016-09-21 | 清华大学 | Turbine engine |
-
2016
- 2016-04-11 CN CN201610222428.XA patent/CN105697148B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19600824A1 (en) * | 1995-09-28 | 1997-07-17 | Gerhard Ittner | Turbine shaft load drive mechanism for hypersonic region |
| EP1532358A2 (en) * | 2002-06-26 | 2005-05-25 | R-Jet Engineering Ltd. | Orbiting combustion nozzle engine |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN103835836A (en) * | 2014-03-10 | 2014-06-04 | 金剑 | Bypass-ratio controllable gas turbine |
| CN205592026U (en) * | 2016-04-11 | 2016-09-21 | 清华大学 | Turbine engine |
Non-Patent Citations (1)
| Title |
|---|
| 外涵装有脉冲爆震加力燃烧室的涡扇发动机热力性能分析;陈文娟等;《西北工业大学学报》;20100430;第28卷(第2期);240-244 * |
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| CN105697148A (en) | 2016-06-22 |
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Effective date of registration: 20190626 Address after: Room 261, Building 2, 3339 Linggongtang Road (Jiaxing Science and Technology City), Nanhu District, Jiaxing City, Zhejiang Province Patentee after: Qinghang Tian (Zhejiang) Technology Co., Ltd. Address before: 100084 Tsinghua Yuan, Beijing, Haidian District Patentee before: Tsinghua University |
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