CN206376947U - Turbogenerator - Google Patents
Turbogenerator Download PDFInfo
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- CN206376947U CN206376947U CN201621423478.6U CN201621423478U CN206376947U CN 206376947 U CN206376947 U CN 206376947U CN 201621423478 U CN201621423478 U CN 201621423478U CN 206376947 U CN206376947 U CN 206376947U
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Abstract
The utility model provides a kind of turbogenerator, and 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 and the internal face formation rotation detonation combustor 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, processing is compressed to the air entered via air inlet in first shell body；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 present utility model, high combustion efficiency, reduce the oil consumption rate of engine, improve the thrust-weight ratio and overall performance of engine.
Description
Technical field
The utility model is related 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, 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, it is having an high regard for for further lifting aero gas turbine engine to propose a kind of compact, lightweight, efficient engine structure form
Where the hope of ratio.
Utility model content
In view of problem present in background technology, the purpose of this utility model is to provide a kind of turbogenerator, it is tied
Structure is compact, high combustion efficiency, has been obviously improved the thrust-weight ratio of engine.
To achieve these goals, the utility model provides a kind of turbogenerator, and it includes：First housing, has
Air inlet, air inlet connection outside atmosphere；Second housing, with exhaust outlet；3rd housing, is fixedly connected on the first housing and
Two housings 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
The internal face formation rotation detonation combustor of three housings, it is outer to receive that rotation detonation combustor is communicated in the air inlet of the first housing
The air in portion；Oil circuit component, it is controlled to be communicated in rotation detonation combustor, to provide fuel to rotation detonation combustor)；Igniting
Device, is fixedly installed on the 3rd housing, for entering the fuel in rotation detonating combustion room and the combustion gas progress of air formation
Igniting, and then combustion gas rotation detonating combustion；Compressor, is arranged in first shell body, to entering via air inlet in first shell body
Air be compressed processing；Turbine, is arranged in second shell body, and the driving backspin transhipment of the gas in second shell body
It is dynamic；And main shaft, for connecting compressor and turbine, so that turbine drives compressor motion, so as to realize to air
Compression is handled.
The beneficial effects of the utility model are as follows：
According in turbogenerator of the present utility model, due to be integrated with continuous rotation pinking technology and by compressor,
Main shaft and turbine set into turbomachine system, the air entered from the air inlet of the first housing flowing to rotation pinking
Before combustion chamber, compressed first in the presence of turbomachine system, then the temperature and pressure of air is correspondingly significantly raised,
So as to enhance the rotation detonating combustion process in rotation detonating combustion room, efficiency of combustion is substantially increased, engine is reduced
Oil consumption rate.In addition, the utilization based on continuous rotation pinking technology, accordingly reduces the series of compressor and turbine, so that
The overall structure quality of turbogenerator is alleviated, the thrust-weight ratio of engine is improved；And 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 turbine
The overall performance of engine.
Brief description of the drawings
Fig. 1 is the overall structure diagram according to turbogenerator of the present utility model, and wherein arrow represents propeller for turboprop
The flow direction of gas in machine；
Fig. 2 is the attachment structure schematic diagram of 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 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
Embodiment
Describe in detail with reference to the accompanying drawings according to turbogenerator of the present utility model.
Referring to figs. 1 to Fig. 5, included according to turbogenerator of the present utility model：First housing 11, with air inlet C11,
Air inlet C11 connects outside atmosphere；Second housing 12, with exhaust outlet C12；3rd housing 13, is fixedly connected on the first housing
11 and second housing 12 and are communicated in the first housing 11 and the second housing 12；Centerbody 14, is arranged in the 3rd housing 13, and in
The outside wall surface of heart body 14 and the internal face formation rotation detonation combustor M11 of the 3rd housing 13, the M11 connections of rotation detonation combustor
In the air inlet C11 of the first housing 11 with receive outside air；Oil circuit component 15, it is controlled to be communicated in rotation detonation combustor
M11, to provide fuel (i.e. fuel oil) to rotation detonation combustor M11；Igniter 16, is fixedly installed on the 3rd housing 13, uses
The combustion gas formed in the fuel and air to entering in rotation detonation combustor M11 is lighted a fire, and then combustion gas rotation pinking combustion
Burn；Compressor 17, is arranged in the first housing 11, to being compressed via the air inlet C11 air entered in the first housing 11
Processing；Turbine 18, is arranged in the second housing 12, and rotary motion under the driving of the 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 to air
Compression processing.
According in turbogenerator of the present utility model, pinking technology is continuously rotated and by compressor due to being integrated with
17th, the turbomachine system that main shaft 19 and turbine 18 are constituted, is flowing from the air inlet C11 of the first housing 11 air entered
Move to before rotation detonation combustor M11, compressed first in the presence of turbomachine system, then the temperature and pressure of air
Correspondingly significantly rise, so as to enhance the rotation detonating combustion process in rotation detonation combustor M11, substantially increases burning
Efficiency, reduces the oil consumption rate of engine.In addition, the utilization based on continuous rotation pinking technology, accordingly reduces compressor 17
With the series of turbine 18, so as to alleviate the overall structure quality of turbogenerator, the thrust-weight ratio of engine is improved；And base
In the setting of turbomachine system so that without after-burner part in turbogenerator, the overall structure of turbogenerator
It is more compact, so as to improve the overall performance of turbogenerator.
According to turbogenerator of the present utility model, in one embodiment, reference picture 1, 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 is formed at the first air-flow and led to
In road 131；Second gas channel 132, connects the first housing 11；And mixed airflow passage 133, for the first gas channel 131
Gas after interior rotation detonating combustion is mixed with the air in the second gas channel 132.Here, enter via air inlet C11
Air in first housing 11, a part of (being used as oxidant) enters in the first gas channel 131 of the 3rd housing 13, and another
Part enters in the second gas channel 132 of the 3rd housing 13.It is quick-fried into the air flow in the first gas channel 131 to rotating
The fuel fed in shake combustion chamber M11 and with oil circuit component 15 is fully blended, and then rotates detonating combustion, the gas stream after burning
Enter in mixed airflow passage 133.Air into the second gas channel 132, has neither part nor lot in rotation detonating combustion, flows directly to
Gas mixing in mixed airflow passage 133 with being flowed into from the first gas channel 131.
According in turbogenerator of the present utility model, the installed position of the first housing 11 and the 3rd housing 13 is (i.e.
The corresponding installation end face of line A-A in Fig. 1) governor motion (not shown) is provided with, enter the He of the first gas channel 131 for adjusting
The air mass flow of second gas channel 132.Here, different operating demand of the governor motion based on turbogenerator, directly changes
The area ratio of first gas channel 131 and the second gas channel 132, so as to adjust into the first gas channel 131 and the second gas
The air mass flow of circulation road 132.
According to turbogenerator of the present utility model, in one embodiment, reference picture 1, centerbody 14 may include：Precursor
f14；Ring body h14, corresponding with ring body h14 with the 3rd housing 13 part forms rotation detonation combustor M11 (i.e. annular firings
Chamber)；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
Precursor f14 outer surface is expanding passage after first reducing with the part of the inner surface formation of corresponding 3rd housing 13, can be prevented
The detonation wave only 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.
According to turbogenerator of the present utility model, 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 receive
Cavity volume 112, houses another group of compressor 17 and is communicated in the first host cavity 111 and the second gas channel 132.Here, first receive
17 pairs of whole air for entering housing of compressor in cavity volume 111 are pressurized, and 17 pairs of compressor in the second host cavity 112
Air that is after being pressurized via the compressor 17 in the first host cavity 111 but being introduced into rotation detonation combustor M11 carries out secondary
Supercharging, so that the air flowed into the second gas channel 132 is pressure-air.Pressure-air in second gas channel 132 with
The gas after rotation detonating combustion in first gas channel 131 enters second shell body after being mixed in mixed airflow passage 133
For driving turbine 18 in 12, turbine 18 drives compressor 17 to move via main shaft 19, so as to realize 17 pairs of compressor
The compression processing of air.
According in turbogenerator of the present utility model, reference picture 1 and Fig. 3, the inner hollow of centerbody 14 is to form
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 that oil circuit component 15 is fed is evaporated processing in prevapourising room 141, then enters via each fuel nozzle ports 142 and rotates
Detonation combustor M11.Remark additionally herein, precursor f14 of multiple fuel nozzle ports 142 along centerbody 14 circumference point
Cloth, can make fuel enter the flow direction of air of the rotation detonation combustor M11 direction with entering rotation detonation combustor M11
In 90 °, fuel is contributed to fully to be blended with air.
According in turbogenerator of the present utility model, reference picture 1, oil circuit component 15 may include：Oil feed line 151,
It is fixedly connected on the precursor f14 of centerbody 14 and is communicated in prevapourising room 141；And nozzle 152, it is arranged at oil feed line 151
The position being connected with centerbody 14 so that fuel in oil feed line 151 enters prevapourising room 141 via nozzle 152.At this
In remark additionally, atomizer is installed, atomizer makes to flow out from nozzle 152 on the nozzle 152 in prevapourising room 141
Fuel oil be atomized, and then the fuel storage after being atomized is in prevapourising room 141 and by detonation combustor M11 high temperature ring
Border is evaporated to gaseous state, then enters via each fuel nozzle ports 142 in rotation detonation combustor M11.
According in turbogenerator of the present utility model, in one embodiment, oil feed line 151 with before centerbody 14
Body f14 is threadedly coupled.But not only limit is in this way, can also be using other connected modes.
According in turbogenerator of the present utility model, in one embodiment, reference picture 1, turbogenerator can also be wrapped
Include：Nozzle component 20, is communicated in the exhaust outlet C12 of the second housing 12, to discharge the gas in the second housing 12.Wherein, via
The gas of the exhaust outlet C12 discharges of second housing 12 still has higher temperature and pressure, can continue swollen in nozzle component 20
It is swollen to accelerate.
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, the outside wall surface of conical inner body 202 and the internal face formation tail gas spout 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 tail gas spout C20 big I 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.
According in turbogenerator of the present utility model, shell 201 can be rotationally connected with the second housing 12 by bearing.
According in turbogenerator of the present utility model, the first housing 11 may be bolted in the 3rd housing 13, second
The bolt connection of housing 12 is in the 3rd housing 13.Main shaft 19 can be rotationally connected with the first housing 11 and the second housing 12 by bearing.
According in turbogenerator of the present utility model, the part corresponding with the blade of compressor 17 of the first housing 11
Settable to have diffuser (not shown), the part corresponding with the blade of turbine 18 of the second housing 12 is settable guider
(not shown).
Finally remark additionally, turbogenerator of the present utility model is compared with conventional turbogenerator, due to adopting
With continuous rotation pinking technology, it has from supercharging performance, and entropy increases minimum under conditions of equal combustion heating amount, increases
The thermal efficiency of cycle of engine, so that the thrust-weight ratio and oil consumption performance of engine are obviously improved.When whirlpool of the present utility model
When turbine is used in aerospace flight vehicle, mobility, the extended flight envelope curve of aircraft can be improved, help to capture system
Sky power.In addition, turbogenerator of the present utility model 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 inwall of the 3rd housing (13)
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), to provide combustion 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)
Combustion gas with air formation is lighted a fire, and then combustion gas rotation detonating combustion；
Compressor (17), is arranged in the first housing (11), to the air entered via air inlet (C11) in the first housing (11)
It is compressed processing；
Turbine (18), is arranged in the second housing (12), and rotary motion under the driving of the 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 processing 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, for adjusting the air into the first gas channel (131) and the second gas channel (132)
Flow.
4. turbogenerator according to claim 2, it is characterised in that centerbody (14) includes：
Precursor (f14)；
Ring body (h14), part corresponding with ring body (h14) with the 3rd housing (13) forms rotation detonation combustor (M11)；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 to form 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), and the fuel fed via oil circuit component (15) is in prevapourising room
(141) processing 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 with the part of the inner surface formation of corresponding 3rd housing (13) first to reduce the outer surface of fusiform precursor (f14)
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 |
|---|---|---|---|
| CN201621423478.6U CN206376947U (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621423478.6U CN206376947U (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206376947U true CN206376947U (en) | 2017-08-04 |
Family
ID=59407390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621423478.6U Active CN206376947U (en) | 2016-12-22 | 2016-12-22 | Turbogenerator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206376947U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762220A (en) * | 2016-12-22 | 2017-05-31 | 清华大学 | Turbogenerator |
| CN113819491A (en) * | 2021-06-26 | 2021-12-21 | 中国人民解放军空军工程大学 | Rotary detonation combustion chamber return-preventing air inlet structure |
-
2016
- 2016-12-22 CN CN201621423478.6U patent/CN206376947U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762220A (en) * | 2016-12-22 | 2017-05-31 | 清华大学 | Turbogenerator |
| CN106762220B (en) * | 2016-12-22 | 2018-11-06 | 清华大学 | Turbogenerator |
| CN113819491A (en) * | 2021-06-26 | 2021-12-21 | 中国人民解放军空军工程大学 | Rotary detonation combustion chamber return-preventing air inlet structure |
| CN113819491B (en) * | 2021-06-26 | 2022-07-26 | 中国人民解放军空军工程大学 | Return-preventing air inlet structure of rotary detonation combustion chamber |
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