CN100549388C - Between height and low-power mode with the turbogenerator with two off-axis line rotating shafts of valve regulation - Google Patents
Between height and low-power mode with the turbogenerator with two off-axis line rotating shafts of valve regulation Download PDFInfo
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- CN100549388C CN100549388C CN 200680029905 CN200680029905A CN100549388C CN 100549388 C CN100549388 C CN 100549388C CN 200680029905 CN200680029905 CN 200680029905 CN 200680029905 A CN200680029905 A CN 200680029905A CN 100549388 C CN100549388 C CN 100549388C
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- turbine system
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Abstract
The invention discloses a kind of turbogenerator (10) of the VTOL of being particularly suitable for aircraft.The core of turbogenerator can comprise two rotating shaft-low pressure (LP) rotating shafts (14) and high pressure (HP) rotating shaft (12)-wherein, and the LP rotating shaft is installed independently away from the HP rotating shaft.Motor can be by regulating diverter valve assemblies (56) and regulating operation by the fuel flow rate of flow direction engine.In the lift mode of operation, LP and HP rotating shaft all can be worked, and in flight cruise mode of operation forward, HP rotating shaft (12) work, LP rotating shaft (14) can be worked or not work according to the required power of flight situation.When having only HP rotating shaft (12) work, LP rotating shaft (14) can utilize adjusting diverter valve assemblies (56) and inlet flow diverter valve assemblies (58) to close.
Description
Background technique
Common helicopter vertical and landing takeoff (VTOL) aircaft configuration is restricted to the flying speed less than 170 joints usually, but can promote than heavy load.Existing inclined rotor VTOL aircaft configuration has the middle flying speed ability of 300 joints, but lifting capacity is less than helicopter.Common lift fan VTOL aircraft has the high-speed flight ability that surpasses 400 joints, but promoting load capacity further reduces.Lift fan VTOL can also have stronger viability, but needs complicated and expensive propulsion system usually.Therefore, need a kind of low motor of cost that is used for the VTOL aircraft, can make the viability of aircraft stronger, and provide the flying speed ability of about 300 joints, the cruising speed of about 150 joints is arranged, and static hover ability is arranged.
U.S. Patent No. 4286430 discloses the turbogenerator with three rotating shafts: low pressure rotating shaft, intermediate rotary shaft and high pressure rotating shaft.High pressure rotating shaft off-axis line is installed, and typically vertical with respect to other rotating shaft.Air inlet scroll guiding pressurized air leads to the high pressure rotating assembly from middle rotating shaft compressor, and similarly, the exhaust of exhaust scroll direct high pressure turbine assembly is also led to the intermediate pressure turbine assembly.
German patent DE 3816967A1 discloses a kind of double-mode Gas Turbine Power equipment that is used for surface car, and it comprises high-pressure turbine motor and low-pressure turbine motor.When normal full load is worked, motor connects into and makes burning support that gas at first compresses in the low-pressure turbine motor, guiding burner into so that further compression in the high-pressure turbine motor before the combustion fuel subsequently, then, at first in the high-pressure turbine motor, expand, and in the low-pressure turbine motor, further expand.By the valve that can walk around the low-pressure turbine engine operation is provided, the fuel economy during partial load can obtain along with produce some power by high compression engine, only drives the required level of accessory unit thereby air and corresponding fuel consumption be reduced to.
U. S. Patent 2748566 discloses a kind of gas turbine engine that is used for watercraft, it comprises first shunting device, and this first shunting device can make the low-pressure compressor system and the flow passage of whole air-flows that enter high-pressure compressor system or air-flow major component disconnect.Motor also comprises second shunting device, and this second shunting device can make the whole or major component of exhaust airstream depart from the low-pressure turbine system, otherwise exhaust airstream will enter the low-pressure turbine system.
Summary of the invention
A general aspect, the present invention relates to a kind of turbogenerator of the VTOL of being particularly suitable for aircraft.This turbogenerator also can be used for other types of aircraft, comprises other type airplane, surface car and ship.According to different embodiments, the core of turbogenerator comprises two rotating shafts (spool)-low pressure (LP) rotating shaft and high pressure (HP) rotating shaft-wherein the LP rotating shaft is installed independently away from the HP rotating shaft.That is to say that LP can separate with the HP rotating shaft, they do not turn round on concentric shafts like this.Motor can utilize a pair of diverter valve assemblies and regulate operation by the fuel flow rate of flow direction engine.Therefore, the output of the power of motor can be crossed the air-flow of motor and be adjusted to low-level and opposite from high level by utilizing airflow redirector valve assembly control flows.In lift (lift) mode of operation, LP and HP rotating shaft all can be worked, and in flight cruise mode of operation forward, HP rotating shaft work, the LP rotating shaft can be worked or not work according to the required power of flight situation.When having only HP rotating shaft work, the LP rotating shaft can utilize diverter valve assemblies to close.Convertible structure can be used for the propelling output of offline mode forward so that produce the lift unit air horsepower output characteristic that is used for vertical lift mode and produce by the obtaining with valve regulation of engine air flow path direction.Can select among the embodiment, the exhaust gas drive that is used for lift unit can be used for vertical lift mode.According to various embodiments, clean effect is with at the lift of aircraft with cruise and have very high power adjustments ratio between the mode of operation, keeps the low-level of fuel consumption simultaneously.
According to various mode of executions, in first mode of operation (for example high-power mode), regulate diverter valve assemblies and guide first Variable quantity of the air-flow of burning into the high-pressure turbine level.In second mode of operation (for example low-power or cruise mode), regulate diverter valve assemblies and guide second Variable quantity of the air-flow of burning into low-power turbine stage.In addition, in first mode of operation, the flow diverter valve assembly can be guided inlet air into the low-pressure compression system of low pressure rotating assembly, and in second mode of operation, the flow diverter valve assembly can depart from low-pressure compression system with inlet air.During to second mode transition, regulate diverter valve assemblies and can reduce the air-flow that leads to high-power turbine system from first pattern when motor, therefore final all air-flows are all guided the low-power turbine system into.
On the one hand, the invention provides a kind of turbogenerator, comprising: the low pressure rotating assembly that comprises low-pressure turbine system and high-power turbine system; The high pressure rotating assembly that comprises high-pressure turbine system and low-power turbine system, its mesolow rotating assembly and high pressure rotating assembly are along different axis orientation; And the adjusting diverter valve assemblies, being used for will be from the gas flow modulation of the burning of high-pressure turbine system to high power and low-power turbine system according to the mode of operation of turbogenerator.
On the other hand, the invention provides a kind of aircraft (for example aircraft, surface car or ship) that comprises turbogenerator, wherein, this turbogenerator comprises: the low pressure rotating assembly that comprises low-pressure turbine system and high-power turbine system; The high pressure rotating assembly that comprises high-pressure turbine system and low-power turbine system, its mesolow rotating assembly and high pressure rotating assembly are along different axis orientation; And the adjusting diverter valve assemblies, being used for will be from the gas flow modulation of the burning of high-pressure turbine system to high power and low-power turbine system according to the mode of operation of turbogenerator.
Description of drawings
Introduce the present invention below in conjunction with accompanying drawing, in the accompanying drawing:
Fig. 1 and 2 is the view of the turbogenerator of various embodiments of the invention;
Fig. 3 is the view of diverter valve assemblies of the turbogenerator of various embodiments of the invention;
Fig. 4 is the view of the VTOL aircraft of various embodiments of the invention; And
Fig. 5 is the cruise view of fan of the propeller fan that can be used for the turbogenerator of various embodiments of the invention.
Embodiment
Various embodiment of the present invention relates to the turbogenerator that is specially adapted to the VTOL aircraft.Such aircraft has lift mode of operation and flight cruise mode of operation forward, and their raise and leave the landing surface in this lift mode of operation, and this forward in the flight cruise pattern they with high-performance cruise (for example 300 joints).By the convertible turbogenerator of introducing below, the VTOL aircraft can use lift fan or rotor to be used for vertical and landing takeoff, can also use the superelevation by-pass ratio ducted fan/propulsion device of embedding to be used for cruise mode.
Fig. 1 is a simplified perspective view, and Fig. 2 is the rough schematic view of the turbogenerator 10 of various embodiments of the invention.Shown in these views, motor 10 can comprise at least high pressure (HP) rotating assembly 12 and low pressure (LP) rotating assembly 14 both.As following described in more detail, these two rotating assemblies 12,14 are preferably along different axis orientation.For example, LP rotating assembly 14 can be with respect to HP rotating assembly 12 transversal orientations.In the embodiment shown, as shown in Figure 2, LP rotating assembly 14 is along the horizontal axis orientation, and HP rotating shaft 12 is alignd with vertical axis.Though rotating shaft is not preferably turned round on concentric shafts, also can carry out other orientation, for example parallel.
HP rotating assembly 12 also can comprise slender pipe oblique crank Z 18, and this slender pipe oblique crank Z 18 is rotatably installed on the housing by bearing.High-pressure compressor system 34 can be fixed on the axle 18 near the air intlet 36 that is used for HP rotating shaft 12.High-pressure compression system 34 can comprise one or more low-pressure shafts to and/or radial compression stages.In addition, high-pressure turbine system 54 can be fixed on the HP axle 18.According to an embodiment, cruise propulsor 42 can be fixed on the outlet end 40 of HP axle 18.Cruise propulsor 42 for example can be propeller fan, ducted fan or propeller cavitation.Gear-box shown in Fig. 2 44 also can be used to carry out the axle deceleration when needed.In another embodiment, be not that cruise propulsor 42 is mechanically connected on the HP axle 18, but cruise propulsor 42 can efficiently mate ground vapour by freely fitted power turbine 38 and be dynamically connected on the HP axle 18, thereby not need gear-box 44.
With reference to figure 2, in high-power mode, air can enter motor 10 by low-pressure admission mouth 20, and passes through sand/dirt separator 46 entering LP compressor system 22 when needs before.After compression, air can and enter HP compressor system 34 by scroll 48.
Fuel can be dispensed in the burner 52, and fuel is introduced with the air that leaves HP compressor system 34 in this burner 52.In a preferred embodiment, can enter by interstage cooler 50 as needs fuel.
After burning, exhaust can be expanded by high-pressure turbine system 54, so that drive HP compressor system 34.Then, the fluid stream (exhaust) after the burning is regulated in the diverter valve assemblies 56 at this by regulating diverter valve assemblies 56, and exhaust redirect to the LP turbine system 26 of LP compressor system 22.After exhaust was through LP turbine system 26, it can expand by high-power turbine system 28, thereby extracting energy is so that drive lift fan or lift rotor (not shown), so the VTOL aircraft can be with lift mode work.The part burning back air that leaves LP turbine system 26 can be diverted to low-power turbine 38, so that drive cruise propulsor 42, this cruise propulsor 42 can be used as rear portion lift bar in VTOL.When turbogenerator 10 was used for aircraft except that the VTOL aircraft, high-power turbine system 28 can be used for providing power to other types of propulsion devices.
When the VTOL aircraft is transformed into when flying forward from vertical rising, motor 10 preferably is adjusted to mid-power mode from high-power mode.In mid-power mode operation, both preferably work on LP rotating assembly 14 and HP rotating assembly 12.According to various embodiments, fuel stream reduces, so the rotating speed of each rotating assembly reduces.When reducing power by the minimizing fuel flow rate, obtain the transition power points, regulate diverter valve assemblies 56 at this transition power points and begin more exhaust is guided to low-power turbine 38 from HP turbine system 54, and make still less gas flow LP turbine 26 and high-power turbine system 28.Come the air-flow of the minimizing of self-regulation diverter valve assemblies 56 to make further the reduction also of rotating speed of LP rotating assembly 14 finally stop.When the LP rotating assembly stopped, motor 10 was with low-power mode or cruise mode work.
In low-power mode or cruise mode, all LP turbine mechanism assemblies (for example LP turbine system 26 and LP compressor system 22) are off-line and no longer participate in engine operation preferably.Regulate the flow passage that diverter valve assemblies 56 can be guided all gas into low-power turbine system 38 and be closed normal supply LP turbine system 26.Then, (or " rotating shaft import ") diverter valve assemblies 58 that flows between LP compressor system 22 and HP compressor system 34 can be closed the air-flow from LP compressor stage 22.Like this, flow diverter valve assembly 58 can be opened the flow passage that leads to import 36, and this import 36 is used under cruise mode to motor 10 air supplies.Under this pattern, HP rotating assembly 12 itself is worked, and guides all blast airs to low-power turbine stage 38.
The interstage cooler 50 of utilization in scroll 48 is optional features, but it can be in the size that the HP rotating assembly is set and obtains to be used for to provide higher performance aspect the better overall cycle efficiency of low fuel consumption more.
Fig. 1 has also represented to comprise the motor of other normal elements, and these parts comprise for example alternator 70, lubricating oil pump 72, FADEC (full administering digital engine controlling unit) 94 etc.
Fig. 3 has represented the energy valve regulation according to various embodiments.This Figure illustrates the valve arrangement in lift (or high power) pattern.Can find out that as shown in the figure flow diverter valve assembly 58 can comprise two valve A and B.Valve A and B for example can be fly valve or block valve.Similarly, regulate diverter valve assemblies 56 and can comprise two valve C and D, they for example also can be fly valve or block valve.In lift mode, as shown in the embodiment of Fig. 3, valve A opens with valve B and closes, and like this, forces the air that enters to lead to HP rotating shaft 12 then by LP compressor system 22.By valve C being opened and valve D being closed, gas is guided high-power turbine system 28 into, so that provide power to lift fan/rotor 60.In (or low-power) pattern of cruising, being provided with of valve will be opposite.Enter air and will lead to HP rotating shaft 12 then by what valve A stopped by valve B, so bypass LP compressor system 22.Gas will be by valve D (because valve C closes) to low-power turbine system 38, so that provide power to cruise propulsor 42 later on.In middle model, valve C and D will open (or partially opening), so that provide power to each turbine system 26,38.Preferably, valve A and B do not open simultaneously, perhaps at least only open simultaneously the very short time.
In Fig. 3, adjusting diverter valve assemblies 56 is expressed as and comprises two valves (C and D), although can only need the valve with double flute road flow divert in other structure.Similarly, flow diverter valve assembly 58 can include only a valve with double flute road flow divert.
When ducted fan was used for forward flight cruise propulsor 42, triple feed inlet can be used for fan flow.Under any circumstance (no matter being that propeller fan or ducted fan are used as cruise propulsor 42 for example), exhaust airstream from power turbine 26,38 preferably guides the fluid stream of discharging with ducted fan that promotes forward or propeller fan to mix, so that the reduction temperature of total exhaust temperature is used to reduce observable signal level.
Regulate diverter valve assemblies 56 and flow diverter valve assembly 58 valve can by control system for example FADEC 94 control.
According on the other hand, various embodiments of the present invention relate to VTOL aircraft 120, and as shown in Figure 4, it comprises above-mentioned turbogenerator 10.The cruise propulsor 42 of in the embodiment of Fig. 4, having represented turbogenerator 10.In the view of Fig. 4, the major component of turbogenerator 10 is blocked by the fuselage of VTOL aircraft 120.
Fig. 5 has represented the embodiment of the exterior section of turbogenerator 10, and wherein cruise propulsor 42 is propeller fans.
Be used for the VTOL aircraft although introduced turbogenerator 10 above, should be appreciated that motor 10 can be used for the aircraft of other type, comprise other type airplane and surface car (for example humvees or tank) and ship, and power station equipment.
Although by the agency of a plurality of embodiments of motor 10, should be appreciated that those skilled in the art are obtaining can to carry out various modification, changes and improvements to these embodiments under the situation of some or all advantages of the present invention.Under the situation that does not break away from the spirit and scope of the invention of being determined by accessory claim, the application will cover all these modification, changes and improvements.
Claims (27)
1. turbogenerator comprises:
The low pressure rotating assembly that comprises low-pressure turbine system and high-power turbine system;
The high pressure rotating assembly that comprises high-pressure turbine system and low-power turbine system, its mesolow rotating assembly and high pressure rotating assembly are along different axis orientation; And
Regulate diverter valve assemblies, being used for will be from the gas flow modulation of the burning of high-pressure turbine system to high power and low-power turbine system according to the mode of operation of turbogenerator.
2. turbogenerator according to claim 1, wherein, described low pressure rotating assembly comprises low-pressure compression system, the high pressure rotating assembly comprises high-pressure compression system, and further comprise the flow diverter valve assembly, be used for guiding inlet air stream into low-pressure compression system and high-pressure compression system according to the mode of operation of turbogenerator.
3. turbogenerator according to claim 2, wherein,
In first mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into high-power turbine system;
In second mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into the low-power turbine system; And
In the 3rd mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into low-power turbine system and high-power turbine system.
4. turbogenerator according to claim 3, wherein,
In first mode of operation, the flow diverter valve assembly is the low-pressure compression system that is used for inlet air is guided into the low pressure rotating assembly; And
In second mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of all burnings into the low-power turbine system, and the flow diverter valve assembly is to be used for air stream is departed from low-pressure compression system.
5. turbogenerator according to claim 4, wherein, described when motor from first mode of operation during to second mode transition, regulating diverter valve assemblies is to be used to reduce the air-flow that leads to high-power turbine system, therefore final all air-flows are all guided the low-power turbine system into.
6. according to the described turbogenerator of arbitrary claim among the claim 1-5, wherein, described adjusting diverter valve assemblies comprises a valve with double flute road flow divert.
7. according to the described turbogenerator of arbitrary claim among the claim 1-5, wherein, described adjusting diverter valve assemblies comprises at least two valves.
8. according to the described turbogenerator of arbitrary claim among the claim 1-5, wherein, described adjusting diverter valve assemblies comprises a valve with double flute road flow divert.
9. according to the described turbogenerator of arbitrary claim among the claim 1-5, wherein, described adjusting diverter valve assemblies comprises at least two valves.
10. according to the described turbogenerator of arbitrary claim among the claim 2-5, wherein, described flow diverter valve assembly comprises at least two valves.
11. according to the described turbogenerator of arbitrary claim among the claim 1-5, wherein, described low pressure rotating assembly is oriented not concentric with the high pressure rotating assembly.
12. the described turbogenerator of arbitrary claim according among the claim 1-5 also comprises the cruise propulsor that is connected on the high pressure rotating assembly.
13. turbogenerator according to claim 12, wherein, described cruise propulsor is mechanically connected on the high pressure rotating assembly.
14. turbogenerator according to claim 12, wherein, described cruise propulsor pneumatically is connected on the high pressure rotating assembly.
15. turbogenerator according to claim 12, wherein, described cruise propulsor comprises at least one in the fan that cruises, propeller fan or the propeller cavitation.
16. the described turbogenerator of arbitrary claim according among the claim 1-5 also comprises:
Scroll, be used to guide air from low-pressure compression system to the high pressure compression system; And
Interstage cooler in scroll is used to introduce fuel.
17. the described turbogenerator of arbitrary claim according among the claim 1-5 also comprises:
Be connected to the cruise propulsor on the high pressure rotating assembly; And
Be connected to the lift fan on the low pressure rotating assembly.
18. the described turbogenerator of arbitrary claim according among the claim 1-5 also comprises:
Be connected to the cruise propulsor on the high pressure rotating assembly; And
Be connected to the lift rotor on the low pressure rotating assembly.
19. an aircraft that comprises turbogenerator, wherein, this turbogenerator comprises:
The low pressure rotating assembly that comprises low-pressure turbine system and high-power turbine system;
The high pressure rotating assembly that comprises high-pressure turbine system and low-power turbine system, its mesolow rotating assembly and high pressure rotating assembly are along different axis orientation; And
Regulate diverter valve assemblies, being used for will be from the gas flow modulation of the burning of high-pressure turbine system to high power and low-power turbine system according to the mode of operation of turbogenerator.
20. aircraft according to claim 19, wherein, described low pressure rotating assembly comprises low-pressure compression system, the high pressure rotating assembly comprises high-pressure compression system, and further comprise the flow diverter valve assembly, be used for guiding inlet air stream into low-pressure compression system and high-pressure compression system according to the mode of operation of turbogenerator.
21. aircraft according to claim 20, wherein,
In first mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into high-power turbine system;
In second mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into the low-power turbine system; And
In the 3rd mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of burning into low-power turbine system and high-power turbine system.
22. aircraft according to claim 21, wherein,
In first mode of operation, the flow diverter valve assembly is the low-pressure compression system that is used for inlet air is guided into the low pressure rotating assembly; And
In second mode of operation, regulating diverter valve assemblies is to be used for guiding the air-flow of all burnings into the low-power turbine system, and the flow diverter valve assembly is to be used for air stream is departed from low-pressure compression system.
23. according to the described aircraft of arbitrary claim among the claim 19-22, wherein, described high pressure rotating assembly comprises freely fitted low-power turbine assembly.
24. according to the described aircraft of arbitrary claim among the claim 19-22, wherein, described aircraft comprises the VTOL aircraft.
25. aircraft according to claim 23, wherein, described aircraft comprises aircraft, and this aircraft comprises:
Be connected to the cruise propulsor on the high pressure rotating assembly; And
Be connected to the lift fan on the low pressure rotating assembly.
26. aircraft according to claim 23, wherein, described aircraft comprises aircraft, and this aircraft comprises:
Be connected to the cruise propulsor on the high pressure rotating assembly; And
Be connected to the lift rotor on the low pressure rotating assembly.
27. according to the described aircraft of arbitrary claim among the claim 19-22, wherein, described aircraft is selected from the group that comprises aircraft, surface car and ship.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US71022305P | 2005-08-22 | 2005-08-22 | |
| US60/710,223 | 2005-08-22 | ||
| US11/505,519 | 2006-08-17 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101243249A CN101243249A (en) | 2008-08-13 |
| CN100549388C true CN100549388C (en) | 2009-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200680029905 Expired - Fee Related CN100549388C (en) | 2005-08-22 | 2006-08-18 | Between height and low-power mode with the turbogenerator with two off-axis line rotating shafts of valve regulation |
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| CN (1) | CN100549388C (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10737797B2 (en) * | 2017-07-21 | 2020-08-11 | General Electric Company | Vertical takeoff and landing aircraft |
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- 2006-08-18 CN CN 200680029905 patent/CN100549388C/en not_active Expired - Fee Related
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| CN101243249A (en) | 2008-08-13 |
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Effective date of registration: 20170928 Address after: Delaware Patentee after: Te Li dablanc engineering Co. Address before: California, USA Patentee before: Teledyne Technologies Inc. |
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