CN104775900B - Compound cycle engine - Google Patents
Compound cycle engine Download PDFInfo
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- CN104775900B CN104775900B CN201410013702.3A CN201410013702A CN104775900B CN 104775900 B CN104775900 B CN 104775900B CN 201410013702 A CN201410013702 A CN 201410013702A CN 104775900 B CN104775900 B CN 104775900B
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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 present invention relates to compound cycle engines.Discuss compound cycle engine comprising output shaft, each limit at least two rotary units, speed turbines and the turbocharger of internal combustion engine.The speed turbines include rotor, and the output shaft between the rotor and two rotary units in the rotary unit is drivingly engaged.The flow path of the exhaust port of each rotary unit and the speed turbines in its rotor upstream is in fluid communication.The outlet of the compressor of the turbocharger is in fluid communication with the ingress port of each rotary unit.The flow path of the entrance of the pressure turbine of the turbocharger and the speed turbines in its rotor downstream is in fluid communication.Also discuss the method for compound at least two rotary engine.
Description
Technical field
Present invention relates generally to compound cycle engines, and relate more specifically to include one or more rotary combustion hairs
This compound cycle engine of motivation.
Background technique
Some compound cycle engines include rotary engine, and the rotary engine is by being located under turbocharger turbine
The turbine of trip carrys out turbocharging and compound.However, it is known that composite rotating engine arrangement usually have it is compound for turbine
Limited available power and/or limited performance, such as when starting before turbocharger is currently running.
Summary of the invention
In one aspect, a kind of compound cycle engine is provided, the compound cycle engine includes: output shaft；At least
Two rotary units, each unit limit internal combustion engine, including hermetically and are rotatably received in intracorporal turn of respective shell
Son, each shell limit ingress port and exhaust port, the rotor of each unit be installed on the output shaft and with
The output shaft is drivingly engaged；Speed turbines including rotor, the rotor and two in the rotary unit
The output shaft between rotary unit is drivingly engaged and supports the circumferential array of the blade extended across flow path, each shell
The exhaust port of body and the flow path for the rotor upstream for being located at the speed turbines are in fluid communication；And turbocharger, it is described
Turbocharger includes the compressor and pressure turbine being drivingly engaged by common axis, the outlet of the compressor and each
The ingress port of shell is in fluid communication and the stream in the rotor downstream of the entrance and speed turbines of the pressure turbine
Road is in fluid communication.
On the other hand, a kind of compound cycle engine is provided, the compound cycle engine includes: speed turbines,
The speed turbines have the rotor for being drivingly engaged to output shaft；At least two rotary engines, each rotary engine
All with hermetically and being rotatably received in the intracorporal rotor of respective shell with air inlet port and exhaust port, each rotation
The rotor of engine is drivingly engaged to the output shaft, and the rotary engine includes being located in the speed along the output shaft
Degree turbine before the first rotary engine and along the output shaft be located in the speed turbines it is subsequent second rotation
Forward motivation；Corresponding exhaust pipe, the corresponding exhaust pipe is in each exhaust port and speed turbines between its rotor upstream
It provides and is in fluid communication；Turbocharger, the turbocharger include the compressor being drivingly engaged by common axis and pressure
Turbine；Inlet duct, the inlet duct is between the outlet of the compressor and the ingress port of each rotary engine
It provides and is in fluid communication；And turbine pipe, outlet and the pressure turbine of the turbine pipe in the speed turbines
Entrance between fluid communication is provided.
It yet still another aspect, providing a kind of method for compound at least two rotary engine, which comprises make whirlpool
It engages with taking turns the pressure turbine and driven compressor in booster；Be limited to the compressor outlet and each rotating engine
Fluid communication between the ingress port of machine；By speed turbines are placed on along output shaft in the rotary engine two
Each rotary engine and the speed turbines are drivingly engaged to the output shaft between a rotary engine；It limits
Fluid communication between the exhaust port of each rotary engine and the entrance of the speed turbines；And limit the speed
Fluid communication between the entrance of the pressure turbine of the outlet and turbocharger of turbine.
Detailed description of the invention
Referring now to the drawings, in the accompanying drawings:
Fig. 1 is the block diagram of compound cycle engine according to specific embodiment；
Fig. 2 is the sectional view of wankel (Wankel) engine according to specific embodiment, and the Wankel engine is available
In compound cycle engine for example 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 compound cycle engine for example 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 compound cycle engine for example 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 yet another embodiment；And
Fig. 8 is the schematic perspective view of compound cycle engine for example as shown in Figure 7 according to specific embodiment.
Specific embodiment
Referring now to figure 1, it is schematically shown that compound cycle engine 10.Compound cycle engine 10 includes rotary unit
12, each unit 12 is limited by orbital internal combustion engine, which, which has, is sealingly engaged in respective housings
Rotor.The rotary unit 12 drives common load.In an illustrated embodiment, common load includes output shaft 16, this is defeated
Shaft can for example be connected to propeller by Speed Decreaser Gearbox (not shown), and the rotor of each unit 12 be joined to it is described defeated
Shaft.
Compound cycle engine 10 further includes turbocharger 18, is formed by compressor 20 and pressure turbine 22, institute
It states compressor 20 and pressure turbine 22 is drivingly interconnected by axis 24.Compressor 20 and turbine 22, which each may each be, has list
A axis separates single-stage system or multilevel device in multiple independent axes in parallel or series, and can be it is centrifugal or
Axial device.In an illustrated embodiment, the axis 24 of turbocharger 18 is rotated independently of common load.Turbocharger 18
Compressor 20 air is compressed before air enters unit 12.
Rotary unit (multiple) 12 forms the core of compound cycle engine 10 and is each provided which in exhaust pulses shape
The exhaust stream of formula.Exhaust stream from unit (multiple) 12 is supplied to the power turbines 26 being in fluid communication with the unit, and
And also drive common load.Power turbines 26 are speed mode turbines, and are also known as impulse turbine machine, and can be
Axial, radial direction or mixed flow turbine.
In speed turbines, the significant pressure drop in blade path is may be not present in fluid deflector.Therefore, speed turbines
With pressure turbine the difference is that, speed whirlpool is not present in the pressure drop occurred on the rotor in pressure turbine
In turbine.Speed turbines usually have the blade with different cross section compared with pressure turbine；For example, with working fluid
It is circulated through the blade, the blade of pressure turbine usually has the variation of flow area, and the blade of speed turbines is usual
With constant flow area；The blade of pressure turbine usually and be not in relation to rotating disk plane it is symmetrical, and speed turbines
Blade it is usually symmetrical.Therefore, each blade of speed turbines 26 forms the bucket pushed by exhaust stream.Power turbines
26 rotor is rotated by impinging on the buckets the power formed on blade by exhaust pulses.Each exhaust pulses as a result,
Provided kinetic energy is used for the rotor of driving power turbine 26, and at the same time applying the smallest back on rotary unit 12
Pressure.
Power turbines 26 are connected to output shaft 16 by the transmission device 28 of suitable type, and the transmission device is, for example,
Planet, star, biasing or angle gear system.The outlet of power turbines 26 and the entrance fluid of turbocharger turbine 22
Connection.Energy is extracted by turbocharger turbine 22 from the exhaust gas for leaving power turbines 26, via connecting shaft 24
To drive compressor 20..
Although it is not shown, air can optionally cycle through the intercooler between compressor 20 and unit 12, and
And compound cycle engine 10 further include: cooling system, for example including for coolant (for example, water-ethylene, oil, air)
The circulatory system, with the shell of each unit 12 of cooling；The oil coolant of internal mechanical part for unit 12；It is 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
(for example, diesel oil, kerosene (jet fuel), equivalent biological fuel) is connected to and the heavy fuel is transferred to unit 12
In, so that combustion chamber is separated into fuel-rich-air mixture near incendiary source and in the leaner mixing at other positions
Object.
In a particular embodiment, each unit 12 is Wankel engine.With reference to Fig. 2, Wankel engine is shown
Exemplary embodiment；It is to be understood that for the unit 12 in compound cycle engine 10 construction (for example, the placement of port,
The quantity of sealing element and placement etc.) it can be with the difference in illustrated embodiment；Each unit 12 can be by addition to Wankel engine
Rotary engine limit.
As shown in Fig. 2, in a particular embodiment, each unit 12 includes the shell 32 for limiting rotor chamber, rotor chamber tool
There is the profile for limiting two salient angles, which is preferably epitrochoid.Rotor 34 is received in rotor chamber.It should
Rotor limits three circumferentially spaced apex 36 and with the general triangular profile for riding out side outward.The vertex
Portion 36 is sealedly engaged with the inner surface of the peripheral wall 38 of shell 32, to form three operating rooms between rotor 34 and shell 32
40。
Rotor 34 is joined to the centrifugation portion 42 of output shaft 16, to execute revolution in bore of stator.The execution of output shaft 16 is used for
The rotation three times of rotor 34 revolved every time.The geometrical axis 44 of rotor 34 biases from the axis 46 of shell 32 and is parallel to this
Axis 46.During each revolution, each room 40 changes on volume, and move around bore of stator with undergo air inlet, compression,
The four-stage of expansion and exhaust.
Air inlet port 48 is provided by peripheral wall 38, to allow compressed air to enter in one of operating room 40.Exhaust
Port 50 is provided for that the exhaust gas from operating room 40 is discharged also by peripheral wall 38.For spark plug or other
Ignition mechanism and channel 52 for one or more fuel injector (not shown) are provided also by peripheral wall 38.Substitution
Property, air inlet port 48, exhaust port 50 and/or channel 52 can be provided by the end wall or side wall 54 of the shell.
In order to effectively operate, operating room 40 is for example by spring-loaded apex seal part 56 and spring-loaded surface
Or seals 58 and end or corner sealing part 60 seal, the apex seal part 56 extends outer to engage from rotor 34
Wall 38, the surface or seals 58 and end or corner sealing part 60 extend from the rotor 34 to engage end wall
54.Rotor 34 further includes at least one spring-loaded oil seal ring 62, is biased against on end wall 54, and the end wall is around use
In the bearing of rotor 34 being located in axis centrifugation portion 42.
Each Wankel engine provides the exhaust stream in relatively long exhaust pulses form；For example, in specific embodiment
In, each Wankel engine has a detonation of every 360 degree rotation of output shaft, and wherein exhaust port is in the big of the rotation
It is stayed open in about 270 degree, therefore about 75% pulse duty factor is provided.Contrastingly, reciprocating 4 reciprocating piston engine
Piston usually have output shaft it is every 720 degree rotation a detonations, wherein exhaust port is in the about 180 degree of the rotation
It stays open, therefore 25% pulse duty factor is provided.In a particular embodiment, the relatively long exhaust arteries and veins of Wankel engine
Punching can be conducive to driving speed power turbines 26.
Pressure ratio across the compound cycle engine with one or more rotary engines or unit can quilt in this way
It limits:
Wherein, PC is the pressure ratio for turbocharger compressor, PRIt is entrance-outlet pressure of rotary engine
Than PPTIt is for power/combined turbine pressure ratio, PTTIt is the pressure ratio for turbocharger turbine.
It was found by the inventors that in the prior art hybrid engine for including one or more rotary engines, wherein
Power turbines are located at the pressure turbine in turbocharger turbine downstream, and wherein each rotary engine has phase
Deng stereometer expansion and compression ratio, the relatively high stereometer compression ratio of rotary engine typically result in the pressure of turbocharger
Pressure ratio (the P as relatively low as possible of contracting machineC), this is limited by the surge pressure ability of rotary engine.As a result, across turbine
Pressure ratio (the P of machinePTPTT) be restricted, which has limited the available power of power turbines.
It authorizes and is incorporated herein by reference in some hybrid engines, such as on August 17th, 2010
United States Patent (USP) 7, shown in 775,044, the stereometer compression ratio of each rotary engine is less than its expansion ratio.Lower body
Bigger pressure ratio (the P of the possibility for the compressor that product meter compression ratio typically results in turbochargerC), this then increases across turbine
Pressure ratio (the P of machinePTPTT).But lower stereometer compression ratio usually makes entrance-outlet pressure ratio of rotary engine
It is reduced PR, this can increase the back pressure on rotary engine due to increased difficult in cleaning exhaust gas and heat is negative
It carries.This construction is generally provided in the low pressure contracting on the rotary engine started before turbocharger is currently running, this can
The performance of compound cycle engine can be limited.
Contrastingly, in compound cycle engine 10, across the pressure ratio P of power turbines 26PTAbout 1, this is
Because it is speed wind turbine.It is used for the uniform pressure ratio P of compressor as a result,C(with consistent with surge pressure ability) and
The identical entrance of rotary unit-outlet pressure ratio PR(minimize the back pressure and heat load on each rotary unit) allows can be used
In the pressure ratio P of the turbine 22 of turbocharger 18TTWith the combined-circulation for wherein power turbines being pressure turbine
The case where engine, is (that is, have the pressure ratio P greater than 1TT) big compared to more.Therefore, speed turbines are used as power turbines
26, which can permit increase, can be used for the compound power of turbine.
In addition, the stereometer compression ratio of rotary unit 12 need not be reduced to realize the turbine that can be used for turbocharger 18
22 this power increases.Thus in a particular embodiment, the stereometer efficiency maximizing of each rotary unit and its heat
Load minimize, and the performance of compound cycle engine 10 on startup will not due to available power increase and be damaged.
It eliminates moreover, speed turbines are used as power turbines 26 in rotary engine and pressure power turbine
The needs of the large volume exhaust collector usually required between machine.This allows power turbines 26 to be located in combined turbine 22
Upstream rather than downstream.
In the specific embodiment that specifically but not exclusively can be suitable for low altitude area, each rotary unit 12 is that have from 6:1
To the Wankel engine of the stereometer compression ratio of 8:1.The Power Recovery of speed turbines 26 can be by having in material limits
Under exhaust gas temperature maximize, and be thereby adapted for this relatively low stereometer compression ratio, this can contribute to increase
Add the power density of Wankel engine and can also improve in the burning at high speed and under heavy fuel.
With reference to Fig. 3-4, compound cycle engine 10 according to specific embodiment is schematically shown.In the embodiment
In, two rotary units 12 including being in Wankel engine form, wherein the two of output shaft 16 centrifugation portion 42 is each other with 180
Degree angularly biases, for balancing compound cycle engine 10.
The rotor blade 64 of speed-power turbine 26 extends across annular flow path 66.In an illustrated embodiment, power
The rotor of turbine 26 is axial rotor, and flow path 66 is axially extending.Exhaust end of the corresponding exhaust pipe 68 from each unit 12
Mouth 50(sees also Fig. 2) extend to the flow path 66 positioned at 64 upstream of rotor blade.Exhaust pipe 68 extends independently of one another.
In order to minimize the distance between power turbines 26 and each rotary unit 12 and thus minimum exhaust pipe 68
Length, power turbines 26 and its transmission device 28 are located between two rotary units 12 along output shaft 16.In shown reality
It applies in example and referring more specifically to Fig. 3, such as the output shaft 16 made of two interconnecting members extends through power turbines
26 and rotary unit 12, wherein centrifugation portion 42 extends from the rest part of output shaft 16, and as the global facility of output shaft or
It is attached to independent manufacture element thereon.
In a particular embodiment and as shown in figure 4, around power turbines 26 shell 84 be attached directly to it is each
The shell 32 of rotary unit 12.This construction can permit relatively short exhaust pipe 68, therefore help to minimize in each rotation
Turn the kinetic energy rejection of the exhaust pulses between unit 12 and power turbines 26.
The outlet of flow path 66 and/or each exhaust pipe 68 is configured to for exhaust pulses being directed on blade 64, to allow to arrange
The rotation of the rotor of gas pulse driving power turbine 26.Difference of each exhaust pipe 68 in the circumference around power turbines 26
It is connected at position with flow path 66.In an illustrated embodiment, the shell 32 of rotary unit 12 is angularly inclined with 180 degree each other
It moves, such as to allow to reduce the thermal deflection of shell 32.Two exhaust ports 50 and exhaust pipe 68 are located in combined-circulation hair as a result,
On the opposite flank of motivation 10.In a particular embodiment, each exhaust pipe 68 axially or substantially axially extends, with further
Minimize its length.
Referring still to Fig. 3-4, pipe 70 extends from the outlet of compressor 20, and is separated into two entrances pipe 72, each entrance
The air inlet port 48(that pipe is all connected to rotary unit 12 sees also Fig. 2).In this embodiment, compressor 20 includes single radial leaf
Wheel 74.Alternatively, compressor 20 may include one or more rotors, have radially, axially or mixed flow blade.
In an illustrated embodiment, the transmission device 28 of power turbines 26 includes: sun gear 76, is attached to power
On the axis of the rotor of turbine 26；And the planetary gear array 78 engaged with sun gear 76.Planetary gear 78 is installed in rotation
On the planet carrier turned, which is drivingly engaged to output shaft 16.Planetary gear 78 is engaged with fixed gear ring 79.In another reality
It applies in example, planetary gear 78 is mounted in fixed carrier, and is engaged with the gear ring for being drivingly engaged to output shaft 16.Transmission
The reduction ratio of device 28 can be chosen to optimize the operation of speed-power turbine 26 and rotary unit 12.
Turbine pipe 80 extends to the entrance of turbocharger turbine 22 from the flow path 66 for being located at 64 downstream of rotor blade.
In this embodiment, turbocharger turbine 22 includes single radial impeller 82..Alternatively, turbocharger turbine
22 may include one or more rotors, have radially, axially or mixed flow blade.
In an illustrated embodiment, turbo-charger shaft 24 extends along the axis different from the axis of output shaft 16.Such as
In specific embodiment shown in Fig. 4, turbo-charger shaft 24 extends transverse to output shaft 16.Turbo-charger shaft 24 can be additionally
The different loads other than the load of output shaft 16 are connected to, are realized as necessary by gearbox.
With reference to Fig. 5-6, it is schematically shown that compound cycle engine 110 according to another embodiment, wherein with aforementioned
Element is indicated by identical appended drawing reference as the element class of compound cycle engine 10, and will no longer be retouched herein
It states.
In this embodiment, three rotary units 12a, b, c, such as Wankel engine as shown in Figure 2 are provided.Power
Turbine 26 and its transmission device 28 are located between two of unit 12, that is, two units 12a, b are arranged in power turbines
26 and transmission device 28 before, and another unit 12c along output shaft 16 be arranged in power turbines 26 and transmission device 28
(Fig. 5) below；Or two units 12a, b are arranged behind power turbines 26 and transmission device 28, and another unit 12c
It is arranged in front of power turbines 26 and transmission device 28 (Fig. 6) along output shaft 16.In an illustrated embodiment, output shaft 16
Centrifugation portion 42 angularly deviated with 120 degree each other, with for balancing compound cycle engine 10.
Each exhaust pipe 68 is independently extended to from the exhaust port 50 of its corresponding units 12a, b, c positioned at rotor blade 64
The flow path 66 of upstream.In the embodiment illustrated in fig. 6, the shell 32 of two adjacent cells 12a, b have same orientation, that is, arrange
Gas port 50 and exhaust pipe 68 are located on the same side of compound cycle engine 110, and the shell that residue unit 12c has
32 are arranged with other interval 180 degrees, and wherein exhaust port 50 and exhaust pipe 68 are located in the opposite of compound cycle engine 110
On side.Each exhaust pipe 68 is connected at the different location around the circumference of power turbines 26 with flow path 66.
The pipe 70 extended from the outlet of compressor 20 is divided into three inlet tubes 72a, b, c, is each connected to corresponding rotation
Turn the air inlet port 48 of unit 12a, b, c.Inlet tube 72a, b on the same side of the main body of compound cycle engine 110
Common portion is shared before being separated into individual tubes 72a, b near entrance 48.
With reference to Fig. 7-8, it is schematically shown that compound cycle engine 210 according to another embodiment, wherein with previously
Element as the element class of the compound cycle engine 10,110 of description is indicated by identical appended drawing reference, and herein will
No longer it is described.
In this embodiment, four rotary units 12d, e, f, g, such as Wankel engine as shown in Figure 2 are provided.Function
Rate turbine 26 and its transmission device 28 are located in tool, and there are two between two groups of unit 12, that is, two units 12d, e are located in
Before power turbines 26 and transmission device 28, and another two unit 12f, g is located in power turbines 26 along output shaft 16
And behind transmission device 28.In an illustrated embodiment, the centrifugation portion 42 of output shaft 16 is angularly deviated with 90 degree each other,
For balancing compound cycle engine 10.
Each exhaust pipe 68 is independently extended to from the exhaust port 50 of its corresponding units 12d, e, f, g positioned at rotor blade
The flow path 66 of 64 upstreams.Exhaust pipe 68 axially or substantially axially extends, to help to minimize its length.In such as Fig. 8 institute
In the embodiment shown, first group of the shell 32 of adjacent cells 12d, e have same orientation, wherein exhaust port 50 and exhaust pipe
68 are located on the same side of compound cycle engine 110.Second group of the shell 32 of adjacent cells 12f, g are relative to first group
It is orientated with 180 degree, wherein exhaust port 50 and exhaust pipe 68 are located on the opposite flank of compound cycle engine 110.Each
Exhaust pipe 68 is connected at the different location around the circumference of power turbines 26 with flow path 66.
The pipe 70 extended from the outlet of compressor 20 is divided into four inlet tubes 72d, e, f, g, is each connected to corresponding
The air inlet port 48 of rotary unit 12d, e, f, g.Inlet tube 72d, e and 72f, the g for being connected to adjacent entries 48 are attached in entrance 48
Common portion is shared closely before being separated into independent pipe.
In the other embodiments having been not shown, turbocharger 18 also drives output shaft 16, such as by making turbine
The pressure turbine 22 of booster 18 is directly connectcted to power turbines 26 or is joined to output shaft by corresponding transmission device
16 realize.In the other embodiments having been not shown, turbocharger and rotary unit are coaxial, but output shaft and whirlpool
Wheel booster shaft is independently of one another, such as output shaft is hollow and around turbo-charger shaft, the turbocharger
Axis extends through the output shaft.
Although having been illustrated with the embodiment with 2,3 and 4 rotary units, can provide in other embodiments more
In 4 rotary units.In a particular embodiment, rotary unit is arranged so that for the rotary unit of even number, edge
Output shaft has the rotary unit of identical quantity in power turbines front and back；Or the rotary unit for Odd number
For, the quantity along rotary unit of the output shaft before power turbines is than the number in the subsequent rotary unit of power turbines
Measure one more or less.This arrangement can permit the length for minimizing exhaust pipe 68, and thus can help to minimize
Power loss between rotary unit and power turbines.
Although it is not shown, various geometric elements can be used to obtain desirable system operability in whole embodiments
Can, such as inlet guide vane, blow-off valve, waste gate, variable turbine machine nozzle etc..
Although it is not shown, speed-power turbine 26 can be with the non-coaxial side in an offset manner of rotary unit 12
Formula installation.Power turbines 26 can be drivingly engaged output by angled (for example, vertical) actuator system
Axis, the actuator system is for example including gearbox and tower axis (tower shaft).
Foregoing description means to be only exemplary, and it would be recognized by those skilled in the art that can be to the implementation
Example makes change, without departing from the range of disclosed invention.By studying present disclosure, the modification fallen within the scope of the present invention
Will it will be apparent to those skilled in the art that and it is this modification be intended to fall in the appended claims.
Claims (20)
1. a kind of compound cycle engine, the compound cycle engine include:
Output shaft；
At least two rotary units, each rotary unit are limited to internal combustion engine, including hermetically and are rotatably received in
The intracorporal engine rotor of respective shell, each shell limit ingress port and exhaust port, and the engine of each rotary unit turns
Son is all installed on the output shaft and is drivingly engaged with the output shaft；
Speed turbines including turbine rotor, the turbine rotor and two at least two rotary unit
The output shaft between a rotary unit is drivingly engaged and supports the circumferential array for extending across the blade of flow path, each
The exhaust port of shell and the flow path for the turbine rotor upstream for being located at the speed turbines are in fluid communication；And
Turbocharger, the turbocharger include the compressor and pressure turbine being drivingly engaged by common axis, institute
The outlet for stating compressor and the ingress port of each shell are in fluid communication, the entrance of the pressure turbine and the speed turbine
The flow path in the turbine rotor downstream of machine is in fluid communication.
2. compound cycle engine according to claim 1, wherein the output shaft is extended through from the speed turbines
It crosses, and the speed turbines are located between described two rotary units along the output shaft.
3. compound cycle engine according to claim 1, wherein each rotary unit is Wankel engine.
4. compound cycle engine according to claim 3, wherein each Wankel engine, which has, to be limited at from 6:
Stereometer compression ratio in the range of 1 to 8:1.
5. compound cycle engine according to claim 1, wherein the axis of the turbocharger is independently of the output
Axis rotation.
6. compound cycle engine according to claim 5, wherein the axis of the turbocharger and the output shaft with
Nonparallel mode extends.
7. compound cycle engine according to claim 1 further includes the common-rail fuel injection for each rotary unit
Device and the heavy fuel source being connected to the fuel injector.
8. compound cycle engine according to claim 1, wherein the shell of described two rotary units is each other with 180
Degree orientation.
9. compound cycle engine according to claim 2, wherein at least two rotary unit is located so that edge
The output shaft is disposed with the rotary unit of identical quantity in the speed turbines front and back.
10. compound cycle engine according to claim 2, wherein at least two rotary unit is located so that
Along the output shaft the rotary unit of the speed turbines arranged in front quantity ratio behind the speed turbines cloth
The quantity one more or less for the rotary unit set.
11. a kind of compound cycle engine, the compound cycle engine include:
Speed turbines, the speed turbines have the turbine rotor for being drivingly engaged to output shaft；
At least two rotary engines, each rotary engine have hermetically and are rotatably received in air inlet port
With the intracorporal engine rotor of respective shell of exhaust port, the engine rotor of each rotary engine is drivingly engaged to described
Output shaft, the rotary engine include the first rotary engine being located in front of the speed turbines along the output shaft
And subsequent second rotary engine of the speed turbines is located in along the output shaft；
Corresponding exhaust pipe, the corresponding exhaust pipe is in each exhaust port and speed turbines between its turbine rotor upstream
It provides and is in fluid communication；
Turbocharger, the turbocharger include the compressor and pressure turbine being drivingly engaged by common axis；
Inlet duct, the inlet duct provide between the outlet of the compressor and the air inlet port of each rotary engine
It is in fluid communication；And
Turbine pipe, the turbine pipe provide between the outlet of the speed turbines and the entrance of the pressure turbine
It is in fluid communication.
12. compound cycle engine according to claim 11, wherein each exhaust pipe axially or substantially axially prolongs
It stretches.
13. compound cycle engine according to claim 11, wherein each rotary engine is Wankel engine.
14. compound cycle engine according to claim 11, wherein the output shaft extends from the speed turbines
It passes through, and the speed turbines are drivingly engaged by transmission device and the output shaft, the transmission device is located in
Between first rotary engine and the second rotary engine.
15. compound cycle engine according to claim 11 further includes the common rail fuel for each rotary engine
Injector and the heavy fuel source being connected to the fuel injector.
16. compound cycle engine according to claim 11, wherein the rotary engine is located so that along described
Output shaft is disposed with the rotary engine of identical quantity in the speed turbines front and back.
17. compound cycle engine according to claim 11, wherein the rotary engine is located so that along described
Output shaft the rotary engine of the speed turbines arranged in front quantity ratio behind the speed turbines cloth
The quantity one more or less for the rotary engine set.
18. a kind of method for compound at least two rotary engine, which comprises
It engages with making the pressure turbine and driven compressor in turbocharger；
The fluid communication being limited between the outlet of the compressor and the ingress port of each rotary engine；
By will be every between two rotary engines that output shaft is placed in the rotary engine by speed turbines
A rotary engine and the speed turbines are drivingly engaged to the output shaft；
Limit the fluid communication between the exhaust port of each rotary engine and the entrance of the speed turbines；And
Limit the fluid communication between the outlet of the speed turbines and the entrance of the pressure turbine of the turbocharger.
19. according to the method for claim 18, further includes: provide the stream between heavy fuel source and each rotary engine
Body connection.
20. according to the method for claim 18, wherein each rotary engine has the model being limited at from 6:1 to 8:1
Enclose interior stereometer compression ratio.
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| CN201410013702.3A CN104775900B (en) | 2014-01-13 | 2014-01-13 | Compound cycle engine |
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| CN201410013702.3A CN104775900B (en) | 2014-01-13 | 2014-01-13 | Compound cycle engine |
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| CN104775900B true CN104775900B (en) | 2019-08-20 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US10240522B2 (en) * | 2015-08-07 | 2019-03-26 | Pratt & Whitney Canada Corp. | Auxiliary power unit with combined cooling of generator |
| US10253687B2 (en) * | 2015-08-07 | 2019-04-09 | Pratt & Whitney Canada Corp. | Auxiliary power unit with electrically driven compressor |
| US9890649B2 (en) * | 2016-01-29 | 2018-02-13 | Pratt & Whitney Canada Corp. | Inlet guide assembly |
| US10570789B2 (en) * | 2016-06-17 | 2020-02-25 | Pratt & Whitney Canada Corp. | 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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| DE19600679A1 (en) * | 1995-03-18 | 1996-09-19 | Rolls Royce Plc | Thrust engine for aircraft with compound cycle |
| US20050198957A1 (en) * | 2004-03-15 | 2005-09-15 | Kim Bryan H.J. | Turbocompound forced induction system for small engines |
| US20070240415A1 (en) * | 2003-02-24 | 2007-10-18 | Pratt & Whitney Canada Corp. | Low volumetric compression ratio integrated turbo-compound rotary engine |
| US20110197849A1 (en) * | 2010-02-16 | 2011-08-18 | Sinewaves, LLC | Co-axial rotary engine |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19600679A1 (en) * | 1995-03-18 | 1996-09-19 | Rolls Royce Plc | Thrust engine for aircraft with compound cycle |
| US20070240415A1 (en) * | 2003-02-24 | 2007-10-18 | Pratt & Whitney Canada Corp. | Low volumetric compression ratio integrated turbo-compound rotary engine |
| US20050198957A1 (en) * | 2004-03-15 | 2005-09-15 | Kim Bryan H.J. | Turbocompound forced induction system for small engines |
| US20110197849A1 (en) * | 2010-02-16 | 2011-08-18 | Sinewaves, LLC | Co-axial rotary engine |
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