CN106762220A - Turbogenerator - Google Patents
Turbogenerator Download PDFInfo
- Publication number
- CN106762220A CN106762220A CN201611198998.6A CN201611198998A CN106762220A CN 106762220 A CN106762220 A CN 106762220A CN 201611198998 A CN201611198998 A CN 201611198998A CN 106762220 A CN106762220 A CN 106762220A
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- Prior art keywords
- housing
- turbogenerator
- centerbody
- air
- communicated
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
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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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
- F02C3/085—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage the turbine being of the radial-flow type (radial-radial)
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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
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
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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
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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
- 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
- F02C7/222—Fuel flow conduits, e.g. manifolds
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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
- 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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
Abstract
The invention provides a kind of turbogenerator, it includes：First housing, with air inlet；Second housing；3rd housing, is fixedly connected on the first housing and the second housing and is communicated in the first housing and the second housing；Centerbody, is arranged in the 3rd housing, and the outside wall surface of centerbody forms rotation detonation combustor with the internal face of the 3rd housing；Oil circuit component, it is controlled to be communicated in rotation detonation combustor；Igniter, for being lighted a fire to the combustion gas that the fuel and air that enter in rotation detonating combustion room are formed, and then combustion gas rotation detonating combustion；Compressor, to being compressed treatment into the air in first shell body via air inlet；Turbine, rotary motion under the driving of the gas in second shell body；And main shaft, for connecting compressor and turbine, so that turbine drives compressor motion.The compact conformation of turbogenerator of the invention, high combustion efficiency, reduce the oil consumption rate of engine, improve the thrust-weight ratio and overall performance of engine.
Description
Technical field
The present invention relates to technical field of engines, more particularly to a kind of turbogenerator.
Background technology
Thrust-weight ratio (ratio of thrust and engine weight) and oil consumption rate are the important fingers for weighing aero gas turbine engine
Mark, they determine the mobility and combat radius (or voyage) of aircraft respectively.Due to present material and the limit of technological level
System, turbine base propulsion mode is heated than being difficult further lifting with the loop parameter such as pressure ratio, cause system thrust be difficult to after
Continuous increase, although the thrust performance that can make engine using modes such as after-burners is significantly improved, causes to start
The oil consumption rate of machine is greatly increased, so that the combat radius and airborne period of aircraft are substantially reduced.Therefore, for turbine base
The important channel that propulsion mode improves thrust-weight ratio is loss of weight.Thermal efficiency of cycle is the key factor for determining engine oil consumption rate.Cause
This, proposes that a kind of compact, lightweight, efficient engine structure form are further to lift having an high regard for for aero gas turbine engine
Where the hope of ratio.
The content of the invention
In view of problem present in background technology, it is an object of the invention to provide a kind of turbogenerator, its structure is tight
Gather, high combustion efficiency, be obviously improved the thrust-weight ratio of engine.
To achieve these goals, the invention provides a kind of turbogenerator, it includes：First housing, with air inlet
Mouthful, air inlet connection outside atmosphere；Second housing, with exhaust outlet；3rd housing, is fixedly connected on the first housing and second shell
Body and it is communicated in the first housing and the second housing；Centerbody, is arranged in the 3rd housing, and the outside wall surface of centerbody and the 3rd shell
The internal face of body forms rotation detonation combustor, and rotation detonation combustor is communicated in the air inlet of the first housing to receive outside
Air；Oil circuit component, it is controlled to be communicated in rotation detonation combustor, provide fuel with to rotation detonation combustor)；Igniter, Gu
Surely it is arranged on the 3rd housing, for being lighted a fire to the combustion gas that the fuel and air that enter in rotation detonating combustion room are formed,
And then combustion gas rotation detonating combustion；Compressor, is arranged in first shell body, to the air entered in first shell body via air inlet
It is compressed treatment；Turbine, is arranged in second shell body, and rotary motion under the driving of gas in second shell body；With
And main shaft, for connecting compressor and turbine, so that turbine drives compressor motion, so as to realize at the compression to air
Reason.
Beneficial effects of the present invention are as follows：
In turbogenerator of the invention, continuously rotate pinking technology and by compressor, main shaft due to being integrated with
And turbine set into turbomachine system, the air entered from the air inlet of the first housing flowing to rotation detonating combustion
Before room, compressed in the presence of turbomachine system first, then the temperature and pressure of air is correspondingly significantly raised, so that
The rotation detonating combustion process in rotation detonating combustion room is enhanced, efficiency of combustion is substantially increased, the consumption of engine is reduced
Oil cut rate.Additionally, the utilization based on continuous rotation pinking technology, accordingly reduces the series of compressor and turbine, so as to mitigate
The overall structure quality of turbogenerator, improves the thrust-weight ratio of engine；And it is based on the setting of turbomachine system so that
Without after-burner part in turbogenerator, the overall structure of turbogenerator is more compact, so as to improve propeller for turboprop
The overall performance of machine.
Brief description of the drawings
Fig. 1 is the overall structure diagram of turbogenerator of the invention, and wherein arrow is represented in turbogenerator
Gas flow direction；
Fig. 2 is the attachment structure schematic diagram of the oil circuit component in Fig. 1 and centerbody；
Fig. 3 is the circumferentially distributed schematic diagram of the fuel nozzle ports on the centerbody in Fig. 1；
Fig. 4 is the circumferential position schematic diagram of the igniter in Fig. 1；
Fig. 5 is the profile after line A-A cutting along Fig. 1, illustrates the installation relation of the first housing and the 3rd housing.
Wherein, description of reference numerals is as follows：
Body after 11 first housing r14
The oil circuit component of 111 first host cavity 15
The oil feed line of 112 second host cavity 151
M11 rotates the nozzle of detonation combustor 152
The igniter of C11 air inlets 16
The compressor of 12 second housing 17
The turbine of C12 exhaust outlets 18
The main shaft of 13 the 3rd housing 19
The nozzle component of 131 first gas channel 20
The shell of 132 second gas channel 201
The conical inner body of 133 mixed airflow passage 202
The governor motion of 14 centerbody 203
The cylinder of 141 prevapourising room 2031
The expansion link of 142 fuel nozzle ports 2032
F14 precursor C20 tail gas spouts
H14 ring bodies
Specific embodiment
Describe turbogenerator of the invention in detail with reference to the accompanying drawings.
Referring to figs. 1 to Fig. 5, turbogenerator of the invention includes：First housing 11, with air inlet C11, air inlet
Mouth C11 connection outside atmospheres；Second housing 12, with exhaust outlet C12；3rd housing 13, is fixedly connected on the He of the first housing 11
Second housing 12 and it is communicated in the first housing 11 and the second housing 12；Centerbody 14, is arranged in the 3rd housing 13, and centerbody
The internal face of 14 outside wall surface and the 3rd housing 13 forms rotation detonation combustor M11, and rotation detonation combustor M11 is communicated in the
The air inlet C11 of one housing 11 with receive outside air；Oil circuit component 15, it is controlled to be communicated in rotation detonation combustor M11, with
Fuel (i.e. fuel oil) is provided to rotation detonation combustor M11；Igniter 16, is fixedly installed on the 3rd housing 13, for entering
The combustion gas for entering to rotate the fuel in detonation combustor M11 and air formation is lighted a fire, and then combustion gas rotation detonating combustion；Calm the anger
Machine 17, is arranged in the first housing 11, to being compressed treatment into the air in the first housing 11 via air inlet C11；Whirlpool
Turbine 18, is arranged in the second housing 12, and rotary motion under the driving of gas in the second housing 12；And main shaft 19,
For connecting compressor 17 and turbine 18, so that turbine 18 drives compressor 17 to move, so as to realize the compression to air
Treatment.
In turbogenerator of the invention, continuously rotate pinking technology and by compressor 17, master due to being integrated with
The turbomachine system of axle 19 and the composition of turbine 18, the air entered from the air inlet C11 of the first housing 11 is being flowed to
Before rotation detonation combustor M11, compressed in the presence of turbomachine system first, then the temperature and pressure of air is corresponding
Ground is significantly raised, and so as to enhance the rotation detonating combustion process in rotation detonation combustor M11, substantially increases burning effect
Rate, reduces the oil consumption rate of engine.Additionally, the utilization based on continuous rotation pinking technology, accordingly reduces the He of compressor 17
The series of turbine 18, so as to alleviate the overall structure quality of turbogenerator, improves the thrust-weight ratio of engine；And be based on
The setting of turbomachine system so that without after-burner part in turbogenerator, the overall structure of turbogenerator is more
It is compact, so as to improve the overall performance of turbogenerator.
Turbogenerator of the invention, in one embodiment, reference picture 1, the 3rd housing 13 is formed with：First air-flow
Passage 131, Collecting Center body 14 simultaneously connects the first housing 11, and rotation detonation combustor M11 is formed at the first gas channel 131
It is interior；Second gas channel 132, connects the first housing 11；And mixed airflow passage 133, for the rotation in the first gas channel 131
Turn the gas after detonating combustion to mix with the air in the second gas channel 132.Here, first shell is entered via air inlet C11
Air in body 11, a part of (as oxidant) enters in the first gas channel 131 of the 3rd housing 13, and another part enters
Enter in the second gas channel 132 of the 3rd housing 13.Into the air flow in the first gas channel 131 to rotating detonating combustion
The fuel fed in the M11 of room and with oil circuit component 15 is fully blended, and then rotates detonating combustion, and the gas after burning flows into mixing
In gas channel 133.Air into the second gas channel 132, has neither part nor lot in rotation detonating combustion, flows directly to gaseous mixture
With the gas mixing flowed into from the first gas channel 131 in circulation road 133.
In turbogenerator of the invention, the installed position of the first housing 11 and the 3rd housing 13 is (i.e. in Fig. 1
The corresponding installation end face of line A-A) governor motion (not shown) is provided with, enter the first gas channel 131 and second for adjusting
The air mass flow of gas channel 132.Here, governor motion is based on the different operating demand of turbogenerator, directly changes first
The area ratio of the gas channel 132 of gas channel 131 and second, so as to adjust logical into the first gas channel 131 and the second air-flow
The air mass flow in road 132.
Turbogenerator of the invention, in one embodiment, reference picture 1, centerbody 14 may include：Precursor f14；Ring
Body h14, rotation detonation combustor M11 (i.e. annular firing chamber) is formed with the part corresponding with ring body h14 of the 3rd housing 13；With
And rear body r14.
In this embodiment, with further reference to Fig. 1 and Fig. 2, the precursor f14 of centerbody 14 can be spindle, fusiform
The part that the outer surface of precursor f14 is formed with the inner surface of corresponding 3rd housing 13 is expanding passage after first reducing, and can be prevented
The detonation wave for only being formed in rotation detonation combustor M11 is back in the first housing 11, so as to avoid detonation wave to calming the anger
The influence of machine 17.
Turbogenerator of the invention, in one embodiment, reference picture 1, compressor 17 can be two groups.First housing
11 can have：First host cavity 111, houses one group of compressor 17 and is communicated in the first gas channel 131；And second host cavity
112, house another group of compressor 17 and be communicated in the first host cavity 111 and the second gas channel 132.Here, the first host cavity
17 pairs of whole air into housing of compressor in 111 are pressurized, and compressor 17 pairs in the second host cavity 112 via
Air that is after the supercharging of compressor 17 in first host cavity 111 but being introduced into rotating detonation combustor M11 carries out secondary booster,
So that it is pressure-air to flow into the air in the second gas channel 132.Pressure-air and the first gas in second gas channel 132
The gas after rotation detonating combustion in circulation road 131 enter after mixing in the mixed airflow passage 133 in second shell body 12 with
For driving turbine 18, turbine 18 drives compressor 17 to move via main shaft 19, so as to realize compressor 17 to air
Compression is processed.
In turbogenerator of the invention, reference picture 1 and Fig. 3, the inner hollow of centerbody 14 is forming pre- steaming
Hair room 141.Centerbody 14 is provided with：Multiple fuel nozzle ports 142, are circumferentially evenly distributed on the precursor f14 of centerbody 14, and each combustion
Material spout 142 is communicated in rotation detonation combustor M11.Wherein, oil circuit component 15 is communicated in prevapourising room 141, via oil circuit
The fuel that component 15 feeds is evaporated treatment in prevapourising room 141, then enters rotation pinking via each fuel nozzle ports 142
Combustion chamber M11.Remark additionally herein, multiple fuel nozzle ports 142 are circumferentially distributed along the precursor f14's of centerbody 14, can
The flow direction for making fuel enter the direction and air into rotation detonation combustor M11 for rotating detonation combustor M11 is in
90 °, fuel is contributed to fully to be blended with air.
In turbogenerator of the invention, reference picture 1, oil circuit component 15 may include：Oil feed line 151, it is fixed
It is connected to the precursor f14 of centerbody 14 and is communicated in prevapourising room 141；And nozzle 152, be arranged at oil feed line 151 with
The position of the connection of centerbody 14, so that the fuel in oil feed line 151 enters prevapourising room 141 via nozzle 152.Mend herein
Explanation is filled, atomizer is installed on the nozzle 152 in prevapourising room 141, atomizer makes the combustion from the outflow of nozzle 152
Oil is atomized, and then the hot environment of fuel storage after being atomized in prevapourising room 141 and by detonation combustor M11 is steamed
It is gaseous state to send out, and is then entered in rotation detonation combustor M11 via each fuel nozzle ports 142.
In turbogenerator of the invention, in one embodiment, the precursor of oil feed line 151 and centerbody 14
F14 is threadedly coupled.But not only limit is in this way, can also use other connected modes.
In turbogenerator of the invention, in one embodiment, reference picture 1, turbogenerator may also include：Spray
Tube assembly 20, is communicated in the exhaust outlet C12 of the second housing 12, to discharge the gas in the second housing 12.Wherein, via second shell
The gas of the exhaust outlet C12 discharges of body 12 still has temperature and pressure higher, expansion can be continued in nozzle component 20 and is accelerated.
In this embodiment, reference picture 1, nozzle component 20 may include：Shell 201, is rotationally connected with the second housing 12；In
Heart cone 202, is contained in shell 201, and the outside wall surface of conical inner body 202 forms tail gas spout with the internal face of shell 201
C20；And governor motion 203, for adjusting position of the shell 201 with respect to the second housing 12 to adjust the big of tail gas spout C20
It is small.Here, different working condition of the big I of tail gas spout C20 based on turbogenerator carries out accommodation.
In this embodiment, with further reference to Fig. 1, governor motion 203 may include：Cylinder 2031, is fixed on the second housing
12；And expansion link 2032, it is fixed on shell 201.
In turbogenerator of the invention, shell 201 can be rotationally connected with the second housing 12 by bearing.
In turbogenerator of the invention, the first housing 11 may be bolted in the 3rd housing 13, the second housing
12 bolt connections are in the 3rd housing 13.Main shaft 19 can be rotationally connected with the first housing 11 and the second housing 12 by bearing.
In turbogenerator of the invention, the part corresponding with the blade of compressor 17 of the first housing 11 can set
Diffuser (not shown) is equipped with, the part corresponding with the blade of turbine 18 of the second housing 12 is settable to have guider (not show
Go out).
Finally remark additionally, turbogenerator of the invention compared with conventional turbogenerator, as a result of
Continuous rotation pinking technology, it has from supercharging performance, and entropy increases minimum under conditions of equal combustion heating amount, increases and starts
The thermal efficiency of cycle of machine, so that the thrust-weight ratio of engine and oil consumption performance are obviously improved.When turbogenerator of the invention
During in aerospace flight vehicle, mobility, the extended flight envelope curve of aircraft can be improved, contribute to denial of the air.This
Outward, during turbogenerator of the invention can be additionally used in airline carriers of passengers or large-scale naval vessels.
Claims (10)
1. a kind of turbogenerator, it is characterised in that turbogenerator includes：
First housing (11), with air inlet (C11), air inlet (C11) connection outside atmosphere；
Second housing (12), with exhaust outlet (C12)；
3rd housing (13), is fixedly connected on the first housing (11) and the second housing (12) and is communicated in the first housing (11) and
Two housings (12)；
Centerbody (14), is arranged in the 3rd housing (13), and the outside wall surface of centerbody (14) and the 3rd housing (13) inwall
Face forms rotation detonation combustor (M11), and rotation detonation combustor (M11) is communicated in the air inlet (C11) of the first housing (11)
With the air outside receiving；
Oil circuit component (15), it is controlled to be communicated in rotation detonation combustor (M11), provide combustion with to rotation detonation combustor (M11)
Material；
Igniter (16), is fixedly installed on the 3rd housing (13), for entering the fuel in rotation detonation combustor (M11)
The combustion gas formed with air is lighted a fire, and then combustion gas rotation detonating combustion；
Compressor (17), is arranged in the first housing (11), to the air entered in the first housing (11) via air inlet (C11)
It is compressed treatment；
Turbine (18), is arranged in the second housing (12), and rotary motion under the driving of gas in the second housing (12)；
And
Main shaft (19), for connecting compressor (17) and turbine (18), so that turbine (18) drives compressor (17) motion,
So as to realize the compression treatment to air.
2. turbogenerator according to claim 1, it is characterised in that the 3rd housing (13) is formed with：
First gas channel (131), Collecting Center body (14) simultaneously connects the first housing (11), and rotation detonation combustor (M11)
It is formed in the first gas channel (131)；
Second gas channel (132), the first housing of connection (11)；And
Mixed airflow passage (133) is logical for the gas and the second air-flow after the rotation detonating combustion in the first gas channel (131)
Air mixing in road (132).
3. turbogenerator according to claim 2, it is characterised in that the peace of the first housing (11) and the 3rd housing (13)
Governor motion is provided with holding position, the air of the first gas channel (131) and the second gas channel (132) is entered for adjusting
Flow.
4. turbogenerator according to claim 2, it is characterised in that centerbody (14) includes：
Precursor (f14)；
Ring body (h14), rotation detonation combustor (M11) is formed with the part corresponding with ring body (h14) of the 3rd housing (13)；With
And
Body (r14) afterwards.
5. turbogenerator according to claim 2, it is characterised in that
Compressor (17) is two groups；
First housing (11) has：
First host cavity (111), houses one group of compressor (17) and is communicated in the first gas channel (131)；
Second host cavity (112), houses another group of compressor (17) and is communicated in the first host cavity (111) and the second gas channel
(132)。
6. turbogenerator according to claim 4, it is characterised in that
The inner hollow of centerbody (14) is forming prevapourising room (141)；
Centerbody (14) is provided with：Multiple fuel nozzle ports (142), are circumferentially evenly distributed on the precursor (f14) of centerbody (14), and
Each fuel nozzle ports (142) are communicated in rotation detonation combustor (M11)；
Wherein, oil circuit component (15) is communicated in prevapourising room (141), via the fuel of oil circuit component (15) infeed in prevapourising room
(141) treatment is evaporated in, then enters rotation detonation combustor (M11) via each fuel nozzle ports (142).
7. turbogenerator according to claim 4, it is characterised in that the precursor (f14) of centerbody (14) is spindle,
Expanded afterwards first to reduce the part that the outer surface of fusiform precursor (f14) is formed with the inner surface of corresponding 3rd housing (13)
Formula passage.
8. turbogenerator according to claim 6, it is characterised in that oil circuit component (15) includes：
Oil feed line (151), is fixedly connected on the precursor (f14) of centerbody (14) and is communicated in prevapourising room (141)；And
Nozzle (152), is arranged at the position being connected with centerbody (14) of oil feed line (151), so that in oil feed line (151)
Fuel via nozzle (152) enter prevapourising room (141).
9. turbogenerator according to claim 1, it is characterised in that turbogenerator also includes：Nozzle component (20),
The exhaust outlet (C12) of the second housing (12) is communicated in, to discharge the gas in the second housing (12).
10. turbogenerator according to claim 9, it is characterised in that nozzle component (20) includes：
Shell (201), is rotationally connected with the second housing (12)；
Conical inner body (202), is contained in shell (201), the outside wall surface of conical inner body (202) and the internal face of shell (201)
Form tail gas spout (C20)；And
Governor motion (203), for adjusting position of the shell (201) with respect to the second housing (12) to adjust tail gas spout (C20)
Size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611198998.6A CN106762220B (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611198998.6A CN106762220B (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
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| Publication Number | Publication Date |
|---|---|
| CN106762220A true CN106762220A (en) | 2017-05-31 |
| CN106762220B CN106762220B (en) | 2018-11-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611198998.6A Active CN106762220B (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869094A (en) * | 2018-07-27 | 2018-11-23 | 清华大学 | Rotate detonation engine |
| CN109252961A (en) * | 2017-07-13 | 2019-01-22 | 通用电气公司 | Continuous pinking formula gas-turbine unit and its assemble method |
| CN110360009A (en) * | 2018-04-11 | 2019-10-22 | 于勇 | Multi fuel runoff impulse turbine engine technology and application |
| CN113551264A (en) * | 2021-07-29 | 2021-10-26 | 厦门大学 | Interstage rotary detonation combustion chamber for ground combustion engine combined cycle |
| CN115342380A (en) * | 2022-07-13 | 2022-11-15 | 清航空天(北京)科技有限公司 | Nonlinear detonation combustion chamber |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103726952A (en) * | 2012-10-11 | 2014-04-16 | 高荣江 | Divided-flow type gas turbine engine |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| US20150167544A1 (en) * | 2013-12-12 | 2015-06-18 | General Electric Company | Tuned cavity rotating detonation combustion system |
| CN206376947U (en) * | 2016-12-22 | 2017-08-04 | 清华大学 | Turbogenerator |
-
2016
- 2016-12-22 CN CN201611198998.6A patent/CN106762220B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103726952A (en) * | 2012-10-11 | 2014-04-16 | 高荣江 | Divided-flow type gas turbine engine |
| US20150167544A1 (en) * | 2013-12-12 | 2015-06-18 | General Electric Company | Tuned cavity rotating detonation combustion system |
| CN104153884A (en) * | 2014-08-06 | 2014-11-19 | 西安热工研究院有限公司 | Rotary knocking gas turbine |
| CN206376947U (en) * | 2016-12-22 | 2017-08-04 | 清华大学 | Turbogenerator |
Non-Patent Citations (1)
| Title |
|---|
| 王健平 等: "连续旋转爆轰发动机的研究进展", 《实验流体力学》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109252961A (en) * | 2017-07-13 | 2019-01-22 | 通用电气公司 | Continuous pinking formula gas-turbine unit and its assemble method |
| CN109252961B (en) * | 2017-07-13 | 2021-11-05 | 通用电气公司 | Continuous detonation gas turbine engine and method of assembling same |
| CN110360009A (en) * | 2018-04-11 | 2019-10-22 | 于勇 | Multi fuel runoff impulse turbine engine technology and application |
| CN108869094A (en) * | 2018-07-27 | 2018-11-23 | 清华大学 | Rotate detonation engine |
| CN113551264A (en) * | 2021-07-29 | 2021-10-26 | 厦门大学 | Interstage rotary detonation combustion chamber for ground combustion engine combined cycle |
| CN115342380A (en) * | 2022-07-13 | 2022-11-15 | 清航空天(北京)科技有限公司 | Nonlinear detonation combustion chamber |
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