CN104775900A - Compound circulating engine - Google Patents
Compound circulating engine Download PDFInfo
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- CN104775900A CN104775900A CN201410013702.3A CN201410013702A CN104775900A CN 104775900 A CN104775900 A CN 104775900A CN 201410013702 A CN201410013702 A CN 201410013702A CN 104775900 A CN104775900 A CN 104775900A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The invention relates to a compound circulating engine. The compound circulating engine comprises an output shaft, at least two rotating units respectively used for limiting an internal combustion engine, a speed turbine and a turbocharger. The speed turbine comprises a motor; and the motor is in driving joint with the output shaft between two of the rotating units. An exhaust port of each rotating unit is communicated with a flow path fluid of the speed turbine at the upstream of the rotor. An outlet of a compressor of the turbocharger is communicated with a fluid in an inlet port of each rotating unit. An inlet of a pressure turbine of the turbocharger is communicated with a flow path fluid of the speed turbine at the downstream of the rotor. The invention further discloses a method for compounding at least two rotating motors.
Description
Technical field
The application relates generally to compound cycle engine, and relates more specifically to this compound cycle engine comprising one or more rotating combustion engine.
Background technique
Some compound cycle engines comprise rotary engine, and this rotary engine comes turbosupercharging and compound by the turbo machine being positioned at turbocharger turbine downstream.But known composite rotating engine arrangement has limited available power for turbine compound and/or limited performance usually, such as, when turbosupercharger startup just before runtime.
Summary of the invention
In one aspect, provide a kind of compound cycle engine, described compound cycle engine comprises: output shaft; At least two rotary units, each unit limits explosive motor, comprise hermetically and the rotor be rotatably received in respective housings, each housing limits ingress port and exhaust port, and the rotor of each unit to be installed on described output shaft and to engage with driving with described output shaft; Comprise the speed turbines of rotor, described output shaft between described rotor with the rotary unit of two in described rotary unit engages and supports the circumferential array striding across the blade that stream extends with driving, and the exhaust port of each housing is communicated with the stream fluid of the rotor upstream being positioned at described speed turbines; And turbosupercharger, described turbosupercharger comprises the compressor and pressure turbine that are engaged with driving by common shaft, the outlet of described compressor is communicated with the ingress port fluid of each housing, and the entrance of described pressure turbine is communicated with the stream fluid in the rotor downstream of described speed turbines.
On the other hand, provide a kind of compound cycle engine, described compound cycle engine comprises: speed turbines, and described speed turbines joins the rotor of output shaft to having driving; At least two rotary engines, each rotary engine has hermetically and is rotatably received in the rotor in the respective housings with air inlet port and exhaust port, the rotor of each rotary engine joins described output shaft to driving, and described rotary engine comprises and is positioned at the first rotary engine before described speed turbines along described output shaft and is positioned at the second rotary engine after described speed turbines along described output shaft; Respective row tracheae, described respective row tracheae provides fluid to be communicated with speed turbines at each exhaust port between its rotor upstream; Turbosupercharger, described turbosupercharger comprises the compressor and pressure turbine that are engaged with driving by common shaft; Inlet pipe, described inlet pipe provides fluid to be communicated with between the outlet and the ingress port of each rotary engine of described compressor; And turbo machine pipe, described turbo machine pipe provides fluid to be communicated with between the outlet and the entrance of described pressure turbine of described speed turbines.
In another, provide a kind of method for compound at least two rotary engines, described method comprises: engage with making the pressure turbine in turbosupercharger and driven compressor; The fluid be limited between the outlet of described compressor and the ingress port of each rotary engine is communicated with; Each rotary engine and described speed turbines is joined to described output shaft with driving by being placed on along output shaft by speed turbines between two rotary engines in described rotary engine; The fluid limited between the exhaust port of each rotary engine and the entrance of described speed turbines is communicated with; And the fluid limited between the outlet of described speed turbines and the entrance of the pressure turbine of described turbosupercharger is communicated with.
Accompanying drawing explanation
With reference now to accompanying drawing, in the accompanying drawings:
Fig. 1 is the block diagram of the compound cycle engine according to specific embodiment;
Fig. 2 is the sectional view of wankel (Wankel) motor according to specific embodiment, and this Wankel engine can be used in such as compound cycle engine as shown in Figure 1;
Fig. 3 is the schematic diagram of the compound cycle engine of Fig. 1 according to specific embodiment;
Fig. 4 is the schematic perspective view of the such as compound cycle engine as shown in Figure 3 according to specific embodiment;
Fig. 5 is the schematic diagram of the compound cycle engine of Fig. 1 according to another embodiment;
Fig. 6 is the schematic perspective view of the such as compound cycle engine as shown in Figure 5 according to specific embodiment;
Fig. 7 is the schematic diagram of the compound cycle engine of Fig. 1 according to another embodiment; And
Fig. 8 is the schematic perspective view of the such as compound cycle engine as shown in Figure 7 according to specific embodiment.
Embodiment
Refer now to Fig. 1, schematically show compound cycle engine 10.Compound cycle engine 10 comprises rotary unit 12, and each unit 12 is limited by orbital internal combustion engine, and this orbital internal combustion engine has the rotor be bonded on hermetically in respective housings.Described rotary unit 12 drives common load.In an illustrated embodiment, common load comprises output shaft 16, and this output shaft is such as connected to propulsion device by Speed Decreaser Gearbox (not shown), and the rotor of each unit 12 joins described output shaft to.
Compound cycle engine 10 also comprises turbosupercharger 18, and it is formed by compressor 20 and pressure turbine 22, and described compressor 20 and pressure turbine 22 are interconnected by axle 24 with driving.Compressor 20 and turbo machine 22 each can be all that there is single axle or the single-stage system separately in multiple independent axes of in parallel or series connection or multilevel device, and can be centrifugal or axial device.In an illustrated embodiment, the axle 24 of turbosupercharger 18 rotates independent of common load.The compressor 20 of turbosupercharger 18 compressed this air before air enters unit 12.
Rotary unit (multiple) 12 forms the core of compound cycle engine 10 and each exhaust stream all provided in exhaust pulses form.Exhaust stream from unit (multiple) 12 is supplied to the power turbines 26 be communicated with this unit fluid, and drives common load.Power turbines 26 is speed mode turbo machines, and is known as impulse turbine machine, and can be axial, radial or mixed flow turbo machine.
In speed turbines, fluid deflector, and there is not the remarkable pressure drop in blade path.Therefore, the difference of speed turbines and pressure turbine is, can not be present in speed turbines occurring in the epitrochanterian pressure drop in pressure turbine.Speed turbines usually has the blade with different cross section compared with pressure turbine; Such as, along with working fluid cycles flows through this blade, the blade of pressure turbine has the change of flow area usually, and the blade of speed turbines has constant flow area usually; Usually and be not in relation to the plane symmetry of rotating disc, and the blade of speed turbines is normally symmetrical for the blade of pressure turbine.Therefore, each blade of speed turbines 26 forms the bucket promoted by exhaust stream.The rotor of power turbines 26 rotates by impacting by exhaust pulses the power formed on blade on blade.Thus, the kinetic energy that each exhaust pulses provides is used to the rotor of driving power turbo machine 26, and on rotary unit 12, applies minimum back pressure simultaneously.
Power turbines 26 is connected to output shaft 16 by the transmission device 28 of suitable type, and described transmission device is such as planet, star, biased or angle gear system.The outlet of power turbines 26 is communicated with the inlet fluid of turbocharger turbine 22.Energy is extracted, to drive compressor 20. via coupling shaft 24 from the exhaust gas leaving power turbines 26 by turbocharger turbine 22.
Although not shown, but air can cycle through the intercooler between compressor 20 and unit 12 alternatively, and compound cycle engine 10 also comprises: cooling system, such as comprise for freezing mixture (such as, water-ethene, oil, air) the circulatory system, to cool the housing of each unit 12; For the oil coolant of the internal mechanical part of unit 12; One or more coolant heat exchanger etc.
The fuel injector (being common rail fuel injector in a particular embodiment) of each unit 12 and heavy fuel source 30(are such as, diesel oil, kerosene (jet fuel), equivalent biological fuel) be communicated with and this heavy fuel is transferred in unit 12, make firing chamber be layered into the rich fuel-air mixture near incendiary source and the comparatively lean mixture at other positions.
In a particular embodiment, each unit 12 is Wankel engines.With reference to figure 2, show the exemplary embodiment of Wankel engine; It being understood that the structure (such as, the placement of port, the quantity of Sealing and placement etc.) for the unit 12 in compound cycle engine 10 can different from illustrated embodiment; Each unit 12 can be limited by the rotary engine except Wankel engine.
As shown in Figure 2, in a particular embodiment, each unit 12 comprises the housing 32 limiting rotor chamber, and this rotor chamber has the profile of restriction two salient angles, and this profile is preferably epitrochoid.Rotor 34 is received in rotor chamber.This rotor limits three isolated apex 36 of circumference and has the general triangular profile outwards encircleing side.Described apex 36 is sealedly engaged with the internal surface of the peripheral wall 38 of housing 32, to form three working rooms 40 between rotor 34 and housing 32.
Rotor 34 joins the centrifugal portion 42 of output shaft 16 to, to perform revolution in stator cavity.Output shaft 16 performs rotating for three times of each revolution being used for rotor 34.The geometrical axis 44 of rotor 34 is biased from the axis 46 of housing 32 and is parallel to this axis 46.During each revolution, each room 40 changes on volume, and around stator cavity motion to experience the four-stage of air inlet, compression, expansion and exhaust.
Air inlet port 48 is provided by peripheral wall 38, enters into one of working room 40 to allow pressurized air.Exhaust port 50 is also provided by peripheral wall 38, for the exhaust gas of discharging from working room 40.For spark plug or other ignition mechanisms and be also provided by peripheral wall 38 for the passage 52 of one or more fuel injector (not shown).Alternatively, air inlet port 48, exhaust port 50 and/or passage 52 are provided by the end wall of this housing or sidewall 54.
In order to effectively operate, working room 40 is such as sealed by spring-loaded apex seal part 56 and spring-loaded surface or seals 58 and end or corner sealing part 60, described apex seal part 56 extends to engage peripheral wall 38 from rotor 34, and described surface or seals 58 and end or corner sealing part 60 extend to engage end wall 54 from described rotor 34.Rotor 34 also comprises at least one spring-loaded oil seal ring 62, and it is biased leans against on end wall 54, and this end wall is around the bearing be positioned in the centrifugal portion 42 of axle for rotor 34.
Each Wankel engine provides the exhaust stream in relatively long exhaust pulses form; Such as, in a particular embodiment, each Wankel engine has every 360 degree of detonations rotated of output shaft, and wherein exhaust port stays open in about 270 degree of this rotation, therefore provides the pulse duty factor of about 75%.Contrastingly the piston of reciprocating 4 reciprocating piston motors has every 720 degree of detonations rotated of output shaft usually, and wherein exhaust port stays open in about 180 degree of this rotation, therefore provides the pulse duty factor of 25%.In a particular embodiment, the relatively long exhaust pulses of Wankel engine can be conducive to actuating speed power turbines 26.
The pressure ratio striding across the compound cycle engine with one or more rotary engine or unit can be defined like this:
Wherein, PC is the pressure ratio for turbocharger compressor, P
rthe entrance-outlet pressure ratio of rotary engine, P
pTthe pressure ratio for power/combined turbine, P
tTit is the pressure ratio for turbocharger turbine.
Inventor has been found that, in the prior art hybrid engine comprising one or more rotary engine, wherein power turbines is the pressure turbine being positioned at turbocharger turbine downstream, and wherein each rotary engine has equal stereometer expansion and compression ratio, the relatively high stereometer compression ratio of rotary engine causes the as far as possible relatively low pressure ratio (P of the compressor of turbosupercharger usually
c), this is limited by the surge pressure ability of rotary engine.Thus, the pressure ratio (P of turbo machine is striden across
pTp
tT) restricted, which has limited power turbines can power.
In some hybrid engines, such as, authorize on August 17th, 2010 and be attached to U. S. Patent 7,775 herein by reference, shown in 044, the stereometer compression ratio of each rotary engine is less than its expansion ratio.Lower stereometer compression ratio usually cause the compressor of turbosupercharger may be larger pressure ratio (P
c), this increases the pressure ratio (P striding across turbo machine then
pTp
tT).But lower stereometer compression ratio makes the entrance-outlet pressure of rotary engine usually than being the P reduced
r, this back pressure that may increase on rotary engine due to the difficulty increased in cleaning exhaust gas and thermal load.This structure is also provided in the low compression on rotary engine that turbosupercharger starts just before runtime usually, and this may limit the performance of compound cycle engine.
Contrastingly, in compound cycle engine 10, stride across the pressure ratio P of power turbines 26
pTapproximately 1, this is because it is speed wind turbine.Thus, the uniform pressure for compressor compares P
cidentical entrance-the outlet pressure of (with consistent with surge pressure ability) and rotary unit compares P
r(to minimize back pressure on each rotary unit and thermal load) allows can be used for the pressure ratio P of the turbo machine 22 of turbosupercharger 18
tTwith there is the situation that wherein power turbines is the compound cycle engine of pressure turbine (that is, there is the pressure ratio P being greater than 1
tT) compare larger.Therefore, speed turbines is used as power turbines 26 can allow to increase the power that can be used for turbine compound.
In addition, the stereometer compression ratio of rotary unit 12 need not reduce this power increase of the turbo machine 22 realizing can be used for turbosupercharger 18.Thus in a particular embodiment, the stereometer efficiency maximizing of each rotary unit and its thermal load minimize, and the performance of compound cycle engine 10 when starting can not be impaired due to the increase of available power.
And, speed turbines is used as the needs that power turbines 26 eliminates the large volume exhaust collector for needs usual between rotary engine and pressure power turbines.This allows power turbines 26 to be positioned at upstream instead of its downstream of combined turbine 22.
Can specifically but not exclusively be suitable in the specific embodiment of low altitude area, each rotary unit 12 be the Wankel engines of the stereometer compression ratio had from 6:1 to 8:1.The Power Recovery of speed turbines 26 can be maximized by the exhaust gas temperature had under material limits, and be suitable for this relatively low stereometer compression ratio thus, this can contribute to the specific power increasing Wankel engine and the burning that can improve under high speed and heavy fuel.
With reference to figure 3-4, the compound cycle engine 10 according to specific embodiment is schematically shown.In this embodiment, comprise two rotary units 12 in Wankel engine form, wherein two of output shaft 16 centrifugal portions 42 are angularly biased with 180 degree each other, for balance compound cycle engine 10.
The rotor blade 64 of speed-power turbo machine 26 strides across annular flow path 66 and extends.In an illustrated embodiment, the rotor of power turbines 26 is axial rotors, and stream 66 axially extends.Respective row tracheae 68 is also shown in Fig. 2 from the exhaust port 50(of each unit 12) extend to the stream 66 being positioned at rotor blade 64 upstream.Outlet pipe 68 extends independently of one another.
Minimize the length of outlet pipe 68 thus in order to the distance between minimum power turbo machine 26 and each rotary unit 12, power turbines 26 and transmission device 28 thereof are positioned between two rotary units 12 along output shaft 16.In the embodiment shown and more specifically with reference to figure 3, the output shaft 16 be such as made up of two interconnecting members extends through power turbines 26 and rotary unit 12, wherein centrifugal portion 42 extends from the remaining part of output shaft 16, and as output shaft one-piece element or be attached to independence on it and manufacture element.
In a particular embodiment and as shown in Figure 4, the shell 84 around power turbines 26 is attached directly to the housing 32 of each rotary unit 12.This structure can allow relatively short outlet pipe 68, therefore contributes to the kinetic energy rejection of the exhaust pulses be minimized between each rotary unit 12 and power turbines 26.
The outlet of stream 66 and/or each outlet pipe 68 is configured as and is directed on blade 64 by exhaust pulses, to allow the rotation of the rotor of exhaust pulses driving power turbo machine 26.Each outlet pipe 68 is communicated with stream 66 at the diverse location place of the circumference around power turbines 26.In an illustrated embodiment, the housing 32 of rotary unit 12 angularly offsets with 180 degree each other, such as, to allow the thermal deflection reducing housing 32.Thus, two exhaust ports 50 and outlet pipe 68 are positioned on the opposite flank of compound cycle engine 10.In a particular embodiment, each outlet pipe 68 axially or roughly axially extends, to minimize its length further.
Still with reference to figure 3-4, pipe 70 extends from the outlet of compressor 20, and is separated into two inlet ducts 72, and the air inlet port 48(that each inlet duct is connected to rotary unit 12 is also shown in Fig. 2).In this embodiment, compressor 20 comprises single radial impeller 74.Alternatively, compressor 20 can comprise one or more rotor, and it has radial direction, axis or mixed flow blade.
In an illustrated embodiment, the transmission device 28 of power turbines 26 comprises: sun gear 76, and it is attached on the axle of the rotor of power turbines 26; And the planetary pinion array 78 to engage with sun gear 76.Planetary pinion 78 is installed on the planet carrier of rotation, and this planet carrier joins output shaft 16 to driving.Planetary pinion 78 engages with fixed gear ring 79.In another embodiment, planetary pinion 78 is arranged in fixed carrier, and engages with join output shaft 16 to gear ring with driving.The reduction speed ratio of transmission device 28 can by the operation selected with optimal speed power turbines 26 and rotary unit 12.
Turbo machine pipe 80 extends to the entrance of turbocharger turbine 22 from the stream 66 being positioned at rotor blade 64 downstream.In this embodiment, turbocharger turbine 22 comprises single radial impeller 82..Alternatively, turbocharger turbine 22 can comprise one or more rotor, and it has radial direction, axis or mixed flow blade.
In an illustrated embodiment, turbo-charger shaft 24 is along the Axis Extension different from the axis of output shaft 16.In specific embodiment as shown in Figure 4, turbo-charger shaft 24 extends transverse to output shaft 16.Turbo-charger shaft 24 additionally can be connected to the different loads except the load of output shaft 16, realizes as necessary by gearbox.
With reference to figure 5-6, schematically show the compound cycle engine 110 according to another embodiment, wherein similar with the element of aforementioned compound cycle engine 10 element is represented by identical reference character, and will no longer be described herein.
In this embodiment, provide three rotary units 12a, b, c, such as Wankel engine as shown in Figure 2.Between two that power turbines 26 and transmission device 28 thereof are positioned at unit 12, namely, two unit 12a, b are arranged on before power turbines 26 and transmission device 28, and another unit 12c is arranged on after power turbines 26 and transmission device 28 (Fig. 5) along output shaft 16; Or two unit 12a, b are arranged on after power turbines 26 and transmission device 28, and another unit 12c is arranged on before power turbines 26 and transmission device 28 (Fig. 6) along output shaft 16.In an illustrated embodiment, the centrifugal portion 42 of output shaft 16 angularly offsets with 120 degree each other, for balance compound cycle engine 10.
Each outlet pipe 68 extends to the stream 66 being positioned at rotor blade 64 upstream independently from the exhaust port 50 of its corresponding units 12a, b, c.In the embodiment illustrated in fig. 6, the housing 32 of two adjacent cells 12a, b has same orientation, namely exhaust port 50 and outlet pipe 68 are positioned on the same side of compound cycle engine 110, and remain housing 32 that unit 12c has and 180 degree, other interval is arranged, wherein exhaust port 50 and outlet pipe 68 are positioned on the opposite flank of compound cycle engine 110.Each outlet pipe 68 is communicated with stream 66 at the diverse location place of the circumference around power turbines 26.
The pipe 70 extended from the outlet of compressor 20 is divided into three inlet ducts 72a, b, c, and each is connected to the air inlet port 48 of corresponding rotary unit 12a, b, c.Inlet duct 72a, the b be positioned on the same side of the main body of compound cycle engine 110 shared public part near entrance 48 before being separated into individual tubes 72a, b.
With reference to figure 7-8, schematically show the compound cycle engine 210 according to another embodiment, wherein similar with the element of previously described compound cycle engine 10,110 element is represented by identical reference character, and will no longer be described herein.
In this embodiment, provide four rotary units 12d, e, f, g, such as Wankel engine as shown in Figure 2.Power turbines 26 and transmission device 28 thereof are positioned between two groups with two unit 12, namely, two unit 12d, e are positioned at before power turbines 26 and transmission device 28, and another two unit 12f, g are positioned at after power turbines 26 and transmission device 28 along output shaft 16.In an illustrated embodiment, the centrifugal portion 42 of output shaft 16 angularly offsets with 90 degree each other, for balance compound cycle engine 10.
Each outlet pipe 68 extends to the stream 66 being positioned at rotor blade 64 upstream independently from the exhaust port 50 of its corresponding units 12d, e, f, g.Outlet pipe 68 axially or roughly axially extends, to contribute to minimizing its length.In the embodiment shown in fig. 8, the housing 32 of first group of adjacent cells 12d, e has same orientation, and wherein exhaust port 50 and outlet pipe 68 are positioned on the same side of compound cycle engine 110.The housing 32 of second group of adjacent cells 12f, g is relative to first group with 180 degree of orientations, and wherein exhaust port 50 and outlet pipe 68 are positioned on the opposite flank of compound cycle engine 110.Each outlet pipe 68 is communicated with stream 66 at the diverse location place of the circumference around power turbines 26.
The pipe 70 extended from the outlet of compressor 20 is divided into four inlet ducts 72d, e, f, g, and each is connected to the air inlet port 48 of corresponding rotary unit 12d, e, f, g.Be connected to inlet duct 72d, e and 72f of adjacent entries 48, g and before being separated into independent pipe, share public part near entrance 48.
In other embodiments be not illustrated, turbosupercharger 18 goes back driver output axle 16, such as, realize by making the pressure turbine 22 of turbosupercharger 18 directly join power turbines 26 to or join output shaft 16 to by corresponding transmission device.In other embodiments be not illustrated, turbosupercharger and rotary unit are coaxial, but output shaft and turbo-charger shaft rotate independently of one another, such as output shaft is hollow and around turbo-charger shaft, this turbo-charger shaft extends through this output shaft.
Although shown the embodiment with 2,3 and 4 rotary units, can provide in other embodiments more than 4 rotary units.In a particular embodiment, rotary unit is arranged so that the rotary unit for even number, has the rotary unit of equal number along output shaft in power turbines front and back; Or for the rotary unit of Odd number, along the quantity one more or less of the rotary unit of number ratio after power turbines of the rotary unit of output shaft before power turbines.This layout can allow the length minimizing outlet pipe 68, and can contribute to the power loss that minimizes between rotary unit and power turbines thus.
Although not shown, in whole embodiment, various geometric element can be used to obtain desirable system operating characteristics, such as inlet guide vane, blow-off valve, wastegate, variable turbine machine nozzle etc.
Although not shown, speed-power turbo machine 26 can with rotary unit 12 in an offset manner and non-coaxial mode is installed.Power turbines 26 can engage output shaft with driving by angled (such as, vertical) actuator system, and this actuator system such as comprises gearbox and tower axle (tower shaft).
Foregoing description means it is only exemplary, and those skilled in the art will recognize that, can make change, and do not depart from disclosed scope of invention to described embodiment.By research present disclosure, the amendment fallen in the scope of the invention will it will be apparent to those skilled in the art that and this amendment is intended to fall in appended claims.
Claims (20)
1. a compound cycle engine, described compound cycle engine comprises:
Output shaft;
At least two rotary units, each unit limits explosive motor, comprise hermetically and the rotor be rotatably received in respective housings, each housing limits ingress port and exhaust port, and the rotor of each unit to be installed on described output shaft and to engage with driving with described output shaft;
Comprise the speed turbines of rotor, described output shaft between described rotor with the rotary unit of two in described rotary unit engages and supports the circumferential array of the blade extending across stream with driving, and the exhaust port of each housing is communicated with the stream fluid of the rotor upstream being positioned at described speed turbines; And
Turbosupercharger, described turbosupercharger comprises the compressor and pressure turbine that are engaged with driving by common shaft, the outlet of described compressor is communicated with the ingress port fluid of each housing, and the entrance of described pressure turbine is communicated with the stream fluid in the rotor downstream of described speed turbines.
2. compound cycle engine according to claim 1, wherein, described output shaft extends through from described speed turbines, and described speed turbines is positioned at along described output shaft between described two rotary units in described rotary unit.
3. compound cycle engine according to claim 1, wherein, each unit is Wankel engine.
4. compound cycle engine according to claim 3, wherein, each Wankel engine has the stereometer compression ratio in the scope that is limited at from 6:1 to 8:1.
5. compound cycle engine according to claim 1, wherein, the axle of described turbosupercharger rotates independent of described output shaft.
6. compound cycle engine according to claim 5, wherein, axle and the described output shaft of described turbosupercharger extend in nonparallel mode.
7. compound cycle engine according to claim 1, also comprises for the common rail fuel injector of each unit and the heavy fuel source that is communicated with described fuel injector.
8. compound cycle engine according to claim 1, wherein, the housing of described two unit in described unit is each other with 180 degree of orientations.
9. compound cycle engine according to claim 2, wherein, described cell location becomes to make the described unit being furnished with equal number along described output shaft in described power turbines front and back.
10. compound cycle engine according to claim 2, wherein, described cell location becomes to make the quantity one more or less of the described unit arranged at described power turbines in the number ratio of the described unit of described power turbines arranged in front along described output shaft below.
11. 1 kinds of compound cycle engines, described compound cycle engine comprises:
Speed turbines, described speed turbines joins the rotor of output shaft to having driving;
At least two rotary engines, each rotary engine has hermetically and is rotatably received in the rotor in the respective housings with air inlet port and exhaust port, the rotor of each rotary engine joins described output shaft to driving, and described rotary engine comprises and is positioned at the first rotary engine before described speed turbines along described output shaft and is positioned at the second rotary engine after described speed turbines along described output shaft;
Respective row tracheae, described respective row tracheae provides fluid to be communicated with speed turbines at each exhaust port between its rotor upstream;
Turbosupercharger, described turbosupercharger comprises the compressor and pressure turbine that are engaged with driving by common shaft;
Inlet pipe, described inlet pipe provides fluid to be communicated with between the outlet and the air inlet port of each rotary engine of described compressor; And
Turbo machine pipe, described turbo machine pipe provides fluid to be communicated with between the outlet and the entrance of described pressure turbine of described speed turbines.
12. compound cycle engines according to claim 11, wherein, each outlet pipe axially or roughly axially extends.
13. compound cycle engines according to claim 11, wherein, each rotary engine is Wankel engine.
14. compound cycle engines according to claim 11, wherein, described output shaft extends through from described speed turbines, and described speed turbines is engaged by transmission device and described output shaft with driving, described transmission device is positioned between described first rotary engine and the second rotary engine.
15. compound cycle engines according to claim 11, also comprise for the common rail fuel injector of each rotary engine and the heavy fuel source that is communicated with described fuel injector.
16. compound cycle engines according to claim 11, wherein, described rotary engine is located so that the described rotary engine being furnished with equal number along described output shaft in described power turbines front and back.
17. compound cycle engines according to claim 11, wherein, described rotary engine is located so that the quantity one more or less of the described rotary engine arranged at described power turbines in the number ratio of the described rotary engine of described power turbines arranged in front along described output shaft below.
18. 1 kinds of methods for compound at least two rotary engines, described method comprises:
Engage with making the pressure turbine in turbosupercharger and driven compressor;
The fluid be limited between the outlet of described compressor and the ingress port of each rotary engine is communicated with;
Each rotary engine and described speed turbines is joined to described output shaft with driving by being placed on along output shaft by speed turbines between two rotary engines in described rotary engine;
The fluid limited between the exhaust port of each rotary engine and the entrance of described speed turbines is communicated with; And
The fluid limited between the outlet of described speed turbines and the entrance of the pressure turbine of described turbosupercharger is communicated with.
19. methods according to claim 18, also comprise: provide the fluid between heavy fuel source with each rotary engine to be communicated with.
20. methods according to claim 18, wherein, each rotary engine has the stereometer compression ratio in the scope that is limited at from 6:1 to 8:1.
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| CN108137161A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | Auxiliary power unit with electrically driven compressor |
| CN108137164A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | The auxiliary power unit of generator cooling with combination |
| CN108884759A (en) * | 2016-01-29 | 2018-11-23 | 普拉特 - 惠特尼加拿大公司 | Entrance guide assembly |
| CN109312622A (en) * | 2016-06-17 | 2019-02-05 | 普拉特 - 惠特尼加拿大公司 | Rotary internal combustion engine with seal lubrication |
| CN110617112A (en) * | 2019-08-27 | 2019-12-27 | 肇庆高新区伙伴汽车技术有限公司 | Gear rotor engine and unit thereof |
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| CN108137161A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | Auxiliary power unit with electrically driven compressor |
| CN108137164A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | The auxiliary power unit of generator cooling with combination |
| CN108884759A (en) * | 2016-01-29 | 2018-11-23 | 普拉特 - 惠特尼加拿大公司 | Entrance guide assembly |
| CN108884759B (en) * | 2016-01-29 | 2020-11-03 | 普拉特-惠特尼加拿大公司 | Inlet guide assembly |
| CN109312622A (en) * | 2016-06-17 | 2019-02-05 | 普拉特 - 惠特尼加拿大公司 | Rotary internal combustion engine with seal lubrication |
| CN109312622B (en) * | 2016-06-17 | 2021-09-21 | 普拉特-惠特尼加拿大公司 | Rotary internal combustion engine with seal lubrication |
| CN110617112A (en) * | 2019-08-27 | 2019-12-27 | 肇庆高新区伙伴汽车技术有限公司 | Gear rotor engine and unit thereof |
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|---|---|
| CN104775900B (en) | 2019-08-20 |
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