CN106321241A - Internal combustion wave rotor turboshaft engine - Google Patents
Internal combustion wave rotor turboshaft engine Download PDFInfo
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- CN106321241A CN106321241A CN201610873096.1A CN201610873096A CN106321241A CN 106321241 A CN106321241 A CN 106321241A CN 201610873096 A CN201610873096 A CN 201610873096A CN 106321241 A CN106321241 A CN 106321241A
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- internal combustion
- rotor
- combustion wave
- wave rotor
- turboshaft engine
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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
- F02C3/16—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 the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
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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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an internal combustion wave rotor turboshaft engine. The internal combustion wave rotor turboshaft engine comprises an internal combustion wave rotor arranged between a gas compressor and a gas turbine. The internal combustion wave rotor comprises a rotor body and two static sealing discs. The rotor body is rotationally arranged on a power output shaft and is in a cylinder shape, and a center shaft of the rotor coincides with the power output shaft. A plurality of channels are arranged on the periphery of the rotor body around the center shaft. The rotor body is provided with an igniter so that gas entering the channels can be ignited to conduct constant-volume combustion. The two static sealing discs are sealed to an inlet and an outlet of the rotor body in a relatively static manner correspondingly. The static sealing disc close to the rotor inlet is provided with a gas inlet port, the static sealing disc close to the rotor outlet is provided with a gas outlet port, and the gas inlet port and the gas outlet port are alternately arranged in the circumferential direction of the center shaft. Constant-pressure combustion of an existing turboshaft engine is replaced with the internal combustion wave rotor, the temperature of a front gas inlet of the turbine does not need to be increased, and the efficiency and performance of the engine can be improved without additionally arranging complex heat regeneration equipment.
Description
Technical field
The present invention relates to aero engine technology field, in particular to a kind of internal combustion wave rotor turboshaft engine.
Background technology
Refering to Fig. 1, the principle schematic of a kind of existing turboshaft engine shown in Fig. 1.As it is shown in figure 1, this whirlpool axle starts
Machine structure is generally: power output shaft 16 and on power output shaft 16 along its compressor 11 axially set gradually, level pressure
Combustor 12, gas turbine 13 and power turbine 14 structure.In the case of intake air flow is certain, existing whirlpool axle starts
Machine performance boost mainly has following approach: one is not change engine structure, improve compressor 11 pressure ratio, improve compressor 11 with
The component efficiencies of turbine；Two is not change engine structure, promotes thermodynamic cycle peak temperature, i.e. combustor peak combustion temperatures
Improve the thermal efficiency of circulation；Three is to change engine structure, uses backheat technology, will motor exhaust after turbine for pre-
Heat enters the air of combustor, improves combustion chambers burn temperature, improves cycle of engine.
Lifting piece efficiency, raising ignition temperature all can effectively promote turboshaft engine performance.But, existing whirlpool axle starts
Compressor in machine 11 and turbine broadly fall into turbomachine, are a kind of mechanical powers and gas internal energy carries out the equipment that converts, its gas
Dynamic the most deep with the research of configuration aspects, that component efficiencies is excavated limited potential.For turbine with combustion chamber components, it is subject to
Being limited to material and cooling, it is the most extremely limited that cycle of engine temperature promotes amplitude, and extremely relies on the development of high-temperature material, it is impossible to
Obtain in a short time and be greatly improved.
Coordinate refering to Fig. 2, the principle schematic of another kind of existing turboshaft engine shown in Fig. 2, i.e. use backheat technology
Improve the turboshaft engine thermal efficiency, promote turboshaft engine performance.As in figure 2 it is shown, this turboshaft engine is above-mentioned existing
Add backheat equipment (such as regenerator 15) and the pipeline of a set of complexity on turboshaft engine, considerably increase engine weight
With structural complexity, it is generally used on ground gas turbine less demanding to weight, consolidating of the most high-power, super high power
Determine power station, ship power and cooling heating and power generation system, restricted application.
Summary of the invention
One main purpose of the present invention is to overcome at least one defect of above-mentioned prior art, it is provided that a kind of efficiency carries
Rise that potentiality are relatively big and the internal combustion wave rotor turboshaft engine of simple in construction.
For achieving the above object, the present invention adopts the following technical scheme that
According to an aspect of the present invention, it is provided that a kind of internal combustion wave rotor turboshaft engine, including power output shaft and
The compressor axially set gradually along it on described power output shaft and gas turbine, it is characterised in that described internal combustion ripple turns
Sub-turboshaft engine also includes internal combustion wave rotor, and it is located between described compressor and described gas turbine, and described internal combustion ripple turns
Attached bag includes rotor and two standstill seal dishes；Described rotor is rotatably arranged on described power output shaft, described rotor in
Cylindric and its central shaft overlaps with described power output shaft, and described rotor outer periphery is provided with multiple passage around described central shaft,
Described rotor is provided with lighter, so that the gas igniting entering described passage is carried out constant volume burning；Said two standstill seal dish
It is sealed in the inlet and outlet of described rotor respectively geo-stationary, sets on the described standstill seal dish of described rotor inlet
There is air inlet port, be provided with air outlet near the described standstill seal dish of described rotor outlet, and described air inlet port and institute
State air outlet to be crisscross arranged on the circumferencial direction around described central shaft.
According to one of them embodiment of the present invention, described internal combustion wave rotor is provided with wave rotor speed governing axle.
According to one of them embodiment of the present invention, the air inlet port of described internal combustion wave rotor goes out with described compressor
Front changeover portion passage it is communicated with between QI KOU.
According to one of them embodiment of the present invention, described front changeover portion passage is gooseneck type, and it is communicated in described pressure
Radial distance between part and the described power output shaft of mechanism of qi is less than its part being communicated in described internal combustion wave rotor and institute
State the radial distance between power output shaft.
According to one of them embodiment of the present invention, the air outlet of described internal combustion wave rotor and described gas turbine
Rear changeover portion passage it is communicated with between air inlet.
According to one of them embodiment of the present invention, described compressor is that twin-stage axial flow-one-stage centrifugal combination type is calmed the anger
Machine.
According to one of them embodiment of the present invention, described gas turbine is single-stage turbine.
According to one of them embodiment of the present invention, described internal combustion wave rotor turboshaft engine also includes air intake duct；Institute
Stating air intake duct and be arranged on the front side of described compressor around described power output shaft, the gas outlet of described air intake duct is communicated in described
The air inlet of compressor.
According to one of them embodiment of the present invention, described internal combustion wave rotor turboshaft engine also includes:
Power turbine, is arranged on the rear side of described gas turbine, entering of described power turbine around described power output shaft
QI KOU is communicated in the gas outlet of described gas turbine.
According to one of them embodiment of the present invention, described power turbine is dual stage turbo.
As shown from the above technical solution, advantage and the good effect of the internal combustion wave rotor turboshaft engine that the present invention proposes exists
In:
The internal combustion wave rotor turboshaft engine that the present invention proposes, in replacing with during by the constant pressure combustion of existing turboshaft engine
Combustion wave rotor, compared with the mode of existing lifting engine performance, uses the turboshaft engine of above-mentioned internal combustion wave rotor, it is not necessary to carry
Rise turbine nose air intake temperature, just can promote efficiency and the performance of electromotor without the backheat equipment increasing complexity.Further,
The internal combustion wave rotor turboshaft engine simple in construction that the present invention proposes, the scope of application is relatively broad.
Accompanying drawing explanation
By being considered in conjunction with the accompanying the following detailed description to the preferred embodiment of the present invention, the various mesh of the present invention
Mark, feature and advantage will become apparent from.Accompanying drawing is only the exemplary diagram of the present invention, is not necessarily to paint in proportion
System.In the accompanying drawings, same reference represents same or similar parts all the time.Wherein:
Fig. 1 is the principle schematic of a kind of existing turboshaft engine；
Fig. 2 is the principle schematic of another kind of existing turboshaft engine；
Fig. 3 is the sectional structure signal according to a kind of internal combustion wave rotor turboshaft engine shown in an illustrative embodiments
Figure；
Fig. 4 is the structure diagram of the internal combustion wave rotor turboshaft engine shown in Fig. 3；
Fig. 5 is the principle schematic of the internal combustion wave rotor turboshaft engine shown in Fig. 3；
Fig. 6 is the structural representation of the internal combustion wave rotor of the internal combustion wave rotor turboshaft engine shown in Fig. 3；
Fig. 7 is the fundamental diagram of the internal combustion wave rotor shown in Fig. 6；
Fig. 8 is the thermodynamic cycle schematic diagram of the gas combustion process of the internal combustion wave rotor shown in Fig. 6.
Wherein, description of reference numerals is as follows:
11. compressors；12. constant pressure combustors；13. gas turbines；14. power turbines；15. regenerators；16. power outputs
Axle；100. power output shaft；200. compressor；300. gas turbine；400. internal combustion wave rotors；410. rotor；420. is static close
Closing disk；421. air inlet port；422. air outlet；430. lighter；440. wave rotor speed governing axles；Changeover portion passage before 450.；
Changeover portion passage after 460.；470. wave rotor bearing lube pipes；480. fuel nozzle；500. air intake duct；600. power turbine；
700. accessory drive.
Detailed description of the invention
Embodiment feature of present invention will describe the most in detail with the exemplary embodiments of advantage.It it should be understood that this
Invention can have various changes in different embodiments, and it neither departs from the scope of the present invention, and explanation therein and
Accompanying drawing is the most illustrative, and is not used to limit the present invention.
Below the different illustrative embodiments to the present invention in description, carrying out referring to the drawings, described accompanying drawing is formed
The part of the present invention, and show the exemplary knot of difference of the many aspects that can realize the present invention the most by way of example
Structure, system and step.It should be understood that, it is possible to use other specified scheme of parts, structure, exemplary means, system and step, and
And structural and functional amendment can be carried out without departing from the scope of the invention.And, although this specification can use
Term " periphery ", " between " etc. different example feature and the element of the present invention are described, but these terms are with in this article
Merely for convenient, the most with reference to the accompanying drawings described in the direction of example.Any content in this specification is not necessarily to be construed that to be needed
The specific three dimensional direction wanting structure just falls within the scope of the present invention.
Refering to Fig. 3, Fig. 3 representatively illustrates the internal combustion wave rotor turboshaft engine of the principle that can embody the present invention
Sectional structure schematic diagram.In this illustrative embodiments, the internal combustion wave rotor turboshaft engine that the present invention proposes is with boat
Illustrate as a example by the turboshaft engine of empty engine art.Skilled addressee readily understands that, for by the present invention
The internal combustion wave rotor turboshaft engine proposed is applied to other field, and following detailed description of the invention is made multiple remodeling,
Add, substitute, delete or other changes, the principle of the internal combustion wave rotor turboshaft engine that these changes still propose in the present invention
In the range of.
As it is shown on figure 3, in the present embodiment, the internal combustion wave rotor turboshaft engine that the present invention proposes mainly includes power
Output shaft 100 and turning along its air intake duct 500 axially set gradually, compressor 200, internal combustion ripple on power output shaft 100
Son 400, gas turbine 300 and power turbine 600.Coordinate refering to Fig. 4 to Fig. 7, Fig. 4 representatively illustrates above-mentioned internal combustion ripple
The structure diagram of rotor turboshaft engine；Fig. 5 representatively illustrates the principle signal of above-mentioned internal combustion wave rotor turboshaft engine
Figure；Fig. 6 representatively illustrates the structural representation of the internal combustion wave rotor 400 of above-mentioned internal combustion wave rotor turboshaft engine；Fig. 7 generation
Show the fundamental diagram of above-mentioned internal combustion wave rotor 400 table.Below in conjunction with accompanying drawing, the internal combustion ripple proposing the present invention turns
Each primary structure of sub-turboshaft engine and operation principle are described in detail.
As shown in Figures 3 to 5, in the present embodiment, internal combustion wave rotor 400 is arranged on compressor 200 and gas turbine
Between 300.Wherein, as shown in Figure 6, this internal combustion wave rotor 400 mainly includes 410, two standstill seal dishes 420 of rotor, igniting
Device 430, front changeover portion passage 450 and rear changeover portion passage 460.Specifically, in the present embodiment, rotor 410 can turn
Be located on power output shaft 100 dynamicly, and rotor 410 cylindrically and its central shaft overlaps with power output shaft 100.Rotor
410 peripheral rings are provided with multiple passage around central shaft.Rotor 410 is provided with lighter 430, the gas igniting entering passage to be carried out
Constant volume burning.It is sealed in the inlet and outlet of rotor 410, near rotor 410 two standstill seal dish 420 geo-stationary respectively
The standstill seal dish 420 of import is provided with air inlet port 421, and the standstill seal dish 420 near rotor 410 outlet is provided with gives vent to anger
Port 422, and air inlet port 421 is being crisscross arranged on the circumferencial direction of central shaft with air outlet 422.Front changeover portion leads to
Road 450 is communicated between the air inlet port 421 of internal combustion wave rotor 400 and the gas outlet of compressor 200, for through compressor
The gas of 200 compressions is entered by front changeover portion passage 450 in the passage of rotor 410.Further, in the present embodiment, this front mistake
The section of crossing passage 450 substantially in gooseneck type, the radial distance between its part being communicated in compressor 200 and power output shaft 100
Radial distance between the part and the power output shaft 100 that are communicated in internal combustion wave rotor 400 less than it.Rear changeover portion passage 460
It is communicated between the air outlet 422 of internal combustion wave rotor 400 and the air inlet of gas turbine 300, in the passage for rotor 410
Gas entered gas turbine 300 by rear changeover portion passage 460.
As shown in Figure 3 and Figure 4, in the present embodiment, air intake duct 500 is arranged on compressor around power output shaft 100
The front side of 200, and the gas outlet of air intake duct 500 is communicated in the air inlet of compressor 200.The gas outlet of compressor 200 is by front
Changeover portion passage 450 is communicated in the air inlet port 421 of internal combustion wave rotor 400.Wherein compressor 200 is preferably twin-stage axial flow-mono-
Level centrifugal combined-type compressor 200.The air inlet of gas turbine 300 is communicated in internal combustion wave rotor by rear changeover portion passage 460
The air outlet 422 of 400, and gas turbine 300 preferably single-stage turbine.Power turbine 600 is arranged around power output shaft 100
At the rear side of gas turbine 300, and the air inlet of power turbine 600 is communicated in the gas outlet of gas turbine 300.Its medium power whirlpool
Wheel 600 is preferably dual stage turbo.It should be noted that in other illustrative embodiments of the present invention, above-mentioned air intake duct
500, the structure such as compressor 200, gas turbine 300 and power turbine 600, all can be selected for existing structure, is not limited thereto.
It should be noted here that the internal combustion wave rotor turboshaft engine shown in accompanying drawing and described in this manual is only
Many examples planted in internal combustion wave rotor turboshaft engine of the principle of the invention can be used.It should be clearly understood that, this
The principle of invention be only limitted to absolutely not internal combustion wave rotor turboshaft engine shown in accompanying drawing or described in this specification any carefully
Joint or any parts of internal combustion wave rotor turboshaft engine.
For example, as shown in Figure 3 and Figure 4, in the present embodiment, internal combustion wave rotor 400 is additionally provided with wave rotor to adjust
Speed axle 440, in order to regulate rotor 410 rotating speed of internal combustion wave rotor 400.
And for example, as it is shown on figure 3, in the present embodiment, internal combustion wave rotor 400 is additionally provided with wave rotor bearing lube pipe
470, in order to the internal bearings of internal combustion wave rotor 400 is carried out oily.
For another example, as it is shown on figure 3, be additionally provided with fuel nozzle 480 in present embodiment, internal combustion wave rotor 400, in order to inwardly
Spray into fuel oil in the passage of the rotor 410 of combustion wave rotor 400, and make fuel oil burn after mixing with gas.
Skilled addressee readily understands that, in order to regulate rotor 410 rotating speed of wave rotor 410, or in order to internally
Combustion wave rotor 400 internal bearings carry out oily, also or in order in the passage to the rotor 410 of internal combustion wave rotor 400 spray
Entering fuel oil, and above-mentioned detailed description of the invention is made multiple remodeling, adds, substitute, delete or other changes, these changes are still
In the range of the principle of the internal combustion wave rotor turboshaft engine of present invention proposition.
Based on the above-mentioned explanation to exemplary embodiment of the invention, the internal combustion wave rotor turboshaft engine that the present invention proposes
Workflow approximately as:
As it is shown in fig. 7, air is entered internal combustion wave rotor turboshaft engine by air intake duct 500, press under compressor 200 acts on
Power raises, and mixes with fuel, enter back into the rotor of internal combustion wave rotor 400 in the front changeover portion passage 450 of content wave rotor 410
In the passage of 410, and in the channel by lighter 430 ignition.In the passage of the rotor 410 of internal combustion wave rotor 400, logical
Cross the effect of the wave system such as shock wave, dilatational wave, supercharging again, mixed gas constant volume burning, combustion gas preexpanding these three process occur also simultaneously
Forming combustion gas, combustion gas is discharged wave rotor 410 by rear changeover portion passage 460.Combustion gas after discharge is through gas turbine 300, by one
Portion of energy is converted into the kinetic energy of gas turbine 300, through power transmission shaft transfer tape dynamic pressure mechanism of qi 200 and the adnexa of gas turbine 300
Actuating device 700.Combustion gas is escaped and enter power turbine 600 by gas turbine 300, does work further, and energy is by power turbine
The output shaft of 600 exports with the form of shaft power.
Gas supercharging again, mixed gas can be completed in parts it should be noted that above-mentioned internal combustion wave rotor 400 is one
Constant volume burning, the parts of combustion gas preexpanding these three process.The present invention utilizes internal combustion wave rotor 400 replacement traditional core scheming, combustion
The burning of material is to complete in the passage of the rotor 410 of wave rotor 410.Compare existing turboshaft engine, at inlet air
In the case of flow is certain, the internal combustion wave rotor turboshaft engine that the present invention proposes need not high-pressure compressor can realize burning
Time pressure increase, and combustion process is to carry out in the passage of the rotor 410 of internal combustion wave rotor 400, it is not necessary to high-pressure turbine
The preexpanding of combustion gas can be realized.The energy exchange of gas is carried out by time-dependent wave system effect, and speed is fast, efficiency is high.Adopt
Can significantly alleviate construction weight with the internal combustion wave rotor turboshaft engine of internal combustion wave rotor 400, improve electromotor power to weight ratio, carry
High engine thermal efficiency, significantly improves engine performance.
It addition, in internal combustion wave rotor 400, the gas after compressor 200 compresses is by the rotor 410 of wave rotor 410
In passage, complicated wave system supercharging again, carries out constant volume burning subsequently in the way of pulse-knocking, and combustion gas will by wave system effect
Energy passes to the live gas after being compressed by compressor 200, and combustion gas expands itself, and temperature is reduced to the design of turbine
Value, final internal combustion wave rotor 400 of discharging, entrance turbine (gas turbine 300 and power turbine 600) acting.
Coordinate with reference to Fig. 8, Fig. 8 representatively illustrate the thermodynamic cycle schematic diagram of the combustion process of internal combustion wave rotor,
Also show the isobaric combustion of available engine and the thermodynamic cycle of the combustion process of isochoric combustion.As shown in Figure 8,1-in figure
2-A-B-3-4 is that internal combustion wave rotor burns, 1-2-3-4 is isochoric combustion, 1-2-3b-4b is isobaric combustion, in figure " A " and " B "
Momentary status point before and after flammable mixed gas firing in the passage of the rotor that point refers respectively to internal combustion wave rotor, fresh mixed gas is from state
Point 2 is pre-compressed to A point (stagnation pressure of A point represents) with PA, and fresh mixed gas isochoric combustion in single channel combustor, from state point A
Being pressurized to B point (stagnation pressure of B point represents with PB) further, the high-temperature fuel gas after burning is expanded to 3 point, then warps from state point B
Turbine expansion does work to 4 points.The passage of the rotor of internal combustion wave rotor only considers straight channel, ignores armature spindle power, i.e. work done during compression
Equal to expansion work (W2-A=WB-3), when compressor delivery temperature (Tt2) and turbine inlet temperature (TIT) (Tt3) and basic engine phase
Meanwhile, the engine thermal release increments under three kinds of burning thermodynamic cycles is identical, but, different thermodynamic cycles cause turbine
The air-flow stagnation pressure of import is inconsistent, and wherein internal combustion wave rotor burning heating power circulatory turbine import stagnation pressure is the highest, demonstrates internal combustion ripple
Rotor can improve gas-turbine unit overall performance, relative to conventional engines thermodynamic cycle process (isobaric combustion), interior
Combustion wave rotor turboshaft engine entropy increase and decrease is little, and output work increases, relative to the electromotor of isochoric combustion (such as pulse-knocking engine
Deng), pressure gain dramatically increases.
In sum, the internal combustion wave rotor turboshaft engine that the present invention proposes, by the constant pressure combustion of existing turboshaft engine
Time replace with internal combustion wave rotor, compared with the mode of existing lifting engine performance, use the whirlpool axle of above-mentioned internal combustion wave rotor to send out
Motivation, it is not necessary to promote turbine nose air intake temperature, just can promote the efficiency of electromotor without the backheat equipment increasing complexity
And performance.Further, the internal combustion wave rotor turboshaft engine simple in construction that the present invention proposes, the scope of application is relatively broad.
Described in detail above and/or illustrate the exemplary enforcement of internal combustion wave rotor turboshaft engine that the present invention proposes
Mode.But embodiments of the present invention are not limited to particular implementation as described herein, on the contrary, the composition of each embodiment
Part and/or step independently and can be used separately with other ingredient as described herein and/or step.One embodiment
Each ingredient and/or each step also can be used in combination with other ingredient of other embodiment and/or step.
When introducing the key element/ingredient/wait of described here and/or diagram, term " ", " one " and " above-mentioned " etc. are in order to table
Show exist one or more key element/ingredient/etc..Term " comprises ", " including " and " having " in order to represent open bag
Include and also can there is other key element/composition portion in the interior meaning and in addition to referring to the key element/ingredient except listing/wait
Point/etc..
Although the internal combustion wave rotor turboshaft engine proposed the present invention according to different specific embodiments is retouched
State, but it will be recognized by those skilled in the art and can enforcement to the present invention change in the spirit and scope of the claims
Dynamic.
Claims (10)
1. an internal combustion wave rotor turboshaft engine, including power output shaft (100) and on described power output shaft (100)
Along its compressor axially set gradually (200) and gas turbine (300), it is characterised in that described internal combustion wave rotor whirlpool axle is sent out
Motivation also includes internal combustion wave rotor (400), and it is located between described compressor (200) and described gas turbine (300), described interior
Combustion wave rotor (400) including:
Rotor (410), is rotatably arranged on described power output shaft (100), and described rotor (410) is cylindrically and its center
Axle overlaps with described power output shaft (100), and described rotor (410) peripheral ring is provided with multiple passage around described central shaft, described
Rotor (410) is provided with lighter (430), so that the gas igniting entering described passage is carried out constant volume burning；And
Two standstill seal dishes (420), are sealed in the inlet and outlet of described rotor (410) respectively geo-stationary, near institute
The described standstill seal dish (420) stating rotor (410) import is provided with air inlet port (421), exports near described rotor (410)
Described standstill seal dish (420) be provided with air outlet (422), and described air inlet port (421) and described air outlet
(422) it is crisscross arranged on the circumferencial direction around described central shaft.
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described internal combustion wave rotor (400)
It is provided with wave rotor speed governing axle (440).
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described internal combustion wave rotor (400)
Air inlet port (421) and the gas outlet of described compressor (200) between be communicated with front changeover portion passage (450).
Internal combustion wave rotor turboshaft engine the most according to claim 3, it is characterised in that described front changeover portion passage
(450) in gooseneck type, the radial direction between its part being communicated in described compressor (200) and described power output shaft (100) away from
Radial distance between the part being communicated in described internal combustion wave rotor (400) less than it and described power output shaft (100).
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described internal combustion wave rotor (400)
Air outlet (422) and the air inlet of described gas turbine (300) between be communicated with rear changeover portion passage (460).
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described compressor (200) is double
Level axial flow-one-stage centrifugal Combined press mechanism of qi (200).
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described gas turbine (300) is
Single-stage turbine.
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described internal combustion wave rotor whirlpool axle is sent out
Motivation also includes:
Air intake duct (500), is arranged on the front side of described compressor (200), described air intake duct around described power output shaft (100)
(500) gas outlet is communicated in the air inlet of described compressor (200).
Internal combustion wave rotor turboshaft engine the most according to claim 1, it is characterised in that described internal combustion wave rotor whirlpool axle is sent out
Motivation also includes:
Power turbine (600), is arranged on the rear side of described gas turbine (300) around described power output shaft (100), described dynamic
The air inlet of power turbine (600) is communicated in the gas outlet of described gas turbine (300).
Internal combustion wave rotor turboshaft engine the most according to claim 9, it is characterised in that described power turbine (600) is
Dual stage turbo.
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| CN201610873096.1A CN106321241A (en) | 2016-09-30 | 2016-09-30 | Internal combustion wave rotor turboshaft engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106939834A (en) * | 2017-03-02 | 2017-07-11 | 南京航空航天大学 | A kind of internal combustion wave rotor and its encapsulating method with mobile end cap |
| CN107131522A (en) * | 2017-06-13 | 2017-09-05 | 南京航空航天大学 | A kind of scroll casing type short distance transition apparatus being used between internal combustion wave rotor and turbine |
| CN112012833A (en) * | 2020-09-10 | 2020-12-01 | 上海和兰透平动力技术有限公司 | Interstage sealing structure of radial-flow gas turbine and simulation design method thereof |
| CN112082765A (en) * | 2020-09-18 | 2020-12-15 | 南京航空航天大学 | Internal combustion wave rotor and experimental device and experimental method thereof |
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