CN1682023A - Jet motor or turbine motor - Google Patents
Jet motor or turbine motor Download PDFInfo
- Publication number
- CN1682023A CN1682023A CN 03821260 CN03821260A CN1682023A CN 1682023 A CN1682023 A CN 1682023A CN 03821260 CN03821260 CN 03821260 CN 03821260 A CN03821260 A CN 03821260A CN 1682023 A CN1682023 A CN 1682023A
- Authority
- CN
- China
- Prior art keywords
- synchronous machine
- jet
- rotor
- turbogenerator
- compressor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
- H02K7/1807—Rotary generators
- H02K7/1823—Rotary generators structurally associated with turbines or similar engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
Abstract
A jet or turbine motor that includes a radial or diagonal compressor containing at least one rotating part pivoted in the fixed part of the jet or turbine motor when a synchronous electromotor containing a mutually cooperating stator and rotor is coupled with at least one rotating part of the compressor where the rotor (200) of the synchronous electromotor (2) is fixed on the rotating part of the jet or turbine motor coupled with the compressor while the stator (201) of the synchronous electromotor (2) is, in alignment with the rotor (200) of the synchronous electromotor (2), placed on a fixed part of the jet or turbine motor and coupled with an electric power supply and/or consumer.
Description
Technical field
The present invention relates to a kind of jet or turbogenerator that has radially (radial) or diagonal angle (diagonal) compressor, described compressor comprises at least one rotating part, be contained in jet or the turbogenerator standing part on, it can be rotated; Synchronous machine with the stator of mutual collaborative work and rotor is connected at least one rotating part of compressor.
Background technique
For having radially or the jet or turbogenerator of diagonal compressors, after the jet or turbogenerator, the initial start (rotation) that needs to guarantee rotor reaches required speed in starting.Making initial start jet or the turbogenerator rotor reach required speed, a lot of technological schemes are arranged is known.
Utilize pressurized air to have multiple by the known schemes of nozzle Driven Compressor blade.Also have some schemes to utilize the effect of pyrope tube on the turbine bucket (pyrope cartridge), its common shaft that rotatablely moves by compressor is delivered to compressor wheels.It also is known using the independent commutator machine that comprises electronic starter, for example, can mechanically connect jet or the turbogenerator axle by gear-box, starting clutch or flywheel clutch.If use said apparatus to be permanently connected to motor jet or the turbogenerator axle, it also can be used to supply electric power (allowing this purposes as fruit structure).Also there are some structures to contain independent motor or independent generator.
There are some shortcomings in above-mentioned structure: the big and big space of needs of weight.Other shortcoming is that the structure of known schemes is quite complicated, the required relevant height of creating conditions, corresponding apparatus cost height.
The objective of the invention is to eliminate or at utmost reduce the shortcoming of prior art.
Summary of the invention
The objective of the invention is to utilize a kind of jet or turbogenerator reaches, its principle is as follows: the rotor of synchronous machine is fixed on the rotating part of the jet or turbogenerator that is connected with compressor, and the stator of the synchronous machine that aligns with the rotor of synchronous machine places on the standing part of jet or turbogenerator and is connected power supply and/or power device.By this configuration, can reduce the space requirement of " synchronous machine-jet or turbogenerator " system, for the rotating part of synchronous machine is installed, also utilize current jet or turbogenerator rotating part to install, make jet or turbogenerator is simplified and cheap.It also is easily that the rotor of synchronous machine is connected to compressor, and does not use other extra equipment, and for example, coupling or gear-box are because utilized the current connection of compressor with jet or the relevant rotating part of turbogenerator.
Considering and simplify jet or turbogenerator structure, will be easily if the rotor of synchronous machine is fixed on the compressor rotating part.
According to a design easily, the rotor of synchronous machine is fixed on the front portion of compressor wheels, and the stator of synchronous machine is fixed on the compressor wheels front.This is convenient to the manufacturing of jet or turbogenerator, particularly is contained in the hollow space of front portion of compressor wheels when the rotor of synchronous machine.
Simultaneously, the stator of synchronous machine is contained in the nappe easily, and nappe is used for the front center that aerodynamics covers compressor wheels, and nappe is fixed on the inlet shell middle part of jet or turbogenerator by radial rib.This scheme is simple, cheap and reliable.
At least one radial rib is a hollow, is used for the lead that load connects synchronous motor stator and power supply and/or power device as pipeline.
The stator of synchronous machine is contained in the housing that hangs on the nappe easily, and this is simple and cheap.
According to a design easily, the rotor of synchronous machine comprises the hollow permanent magnet with even number of poles, the stator of synchronous machine comprises the electromagnet with polyphase windings, and described polyphase windings is arranged in the rotor cavity of synchronous machine, and polyphase windings is connected to power supply and/or power device.This scheme is particularly suitable for built-in synchronous machine is applied to the compressor wheels front portion.
Design easily according to another, the rotor of synchronous machine comprises the permanent magnet with even number of poles, and be arranged in the cavity of synchronous motor stator, and the stator of synchronous machine comprises the hollow electromagnet with polyphase windings, polyphase windings is connected to power supply and/or power device.This design is suitable for: the built-in synchronous machine in the above-mentioned compressor wheel front portion, and the rotor of synchronous machine is contained on the compressor shaft of compressor wheels back for example, perhaps become another rotating part of the jet or turbogenerator that is connected with compressor, for example, become the turbine on the common shaft with compressor, or the like.
In order to cool off the part of synchronous machine, if, then be easily for the stator and/or the rotor of synchronous machine provides cooling pipe system.
This cover of the present invention overall merit jet or turbogenerator is to reach higher electrical efficiency and does not have maintenance operation.The present invention's another advantage jet or turbogenerator is a synchronous machine torque height, and the synchronous machine with permanent magnet can be used as generator and move under high speed, and additionally need not cause the band that magnetic gap increases between synchronous motor stator and the rotor.Less magnetic gap can use the magnet of less thickness to reach identical output.
Description of drawings
The graphic representation of technical solution of the present invention in the accompanying drawings.Fig. 1 represents to have the single shaft air breathing engine embodiment's of synchronous machine longitudinal profile, and synchronous machine constitutes the electric starter of the suction port of compressor part that is integrated in air breathing engine.Fig. 1 represents along the sectional view of hollow radial rib.
Embodiment
To describe a design implementation example of air breathing engine below, it has compressor section 10 and turbo machine part 11, between the two, has firing chamber 13 on the air flue of compressor compresses, and fuel nozzle 14 has outlet in this firing chamber.Firing chamber 13 also has suitable ignition system, and this is expression in the drawings, is used for the combustion air compressed mixture with fuel of initial point.
The spin axis of air breathing engine and radial compressor rotating part is provided with the rotor 200 of synchronous machine 2 alignedly.The rotor 200 of synchronous machine 2 is fixed on the suitable rotating part that connects compressor on the air breathing engine, for example, it is contained on the compressor wheels, or is contained on the common shaft 17 of compressor or turbo machine or connects on the air breathing engine on the other rotating part of compressor.The rotor 200 of synchronous machine 2 rotates with the rotating part of compressor, for the required pivot of synchronous machine 2 operations, uses the pivot of air breathing engine appropriate section, for example, and the pivot of the rotation of compressor or common shaft 17, or the like.
In illustrated embodiment, the rotor 200 of synchronous machine 2 is fixed on the front portion of the wheel 15 of radial compressor, perhaps is fixed in the anterior hollow space of wheel 15 of radial compressor.In illustrated embodiment, the rotor 200 that is fixed on the synchronous machine 2 in the anterior hollow space of wheel 15 of radial compressor comprises the magnet ring 20 on the inwall of anterior hollow space of the wheel 15 that is installed in radial compressor.On magnet ring 20, two permanent magnets 21 are housed along direction towards the hollow space free space.In a not shown design implementation example, the rotor 200 of synchronous machine 2 is fixed on the common shaft 17 with turbo machine, perhaps be contained on the turbo machine, or the like.
In the appropriate section of air breathing engine, the stator 201 of synchronous machine 2 is fixed on the stationary part of air breathing engine.The axle of a pair of stator 201 of synchronous machine and rotor 200 aligns and interlocking by known mode, thereby uses as synchronous machine 2.
In illustrated design implementation example, the stator 201 of synchronous machine 2 is fixed on the anterior front of the wheel 15 of radial compressor, for example in nappe 240.Nappe 240 is used for the front center that aerodynamics covers the wheel 15 of radial compressor, and is contained in the middle part of inlet shell 24 of the radial compressor front of air breathing engine by radial rib 27.Stator has polyphase windings 23, thus in the cavity between the permanent magnet 21 of the rotor 200 of the synchronous machine 2 installed in the anterior hollow space of the wheel 15 of radial compressor of stator 201.For example, pass the lead 25 of a hollow radial rib 27 by use, polyphase windings 23 connects the power subsystem of air breathing engine actual bodies outside.In illustrated embodiment, on the housing 29 that polyphase windings 23 is utilized bolt 30 to be contained in to be suspended in the nappe 240.
The stator 201 of synchronous machine 2 and the cooling of rotor 200 are guaranteed by suitable mode.For example, in illustrated embodiment, the cooling that guarantees stator 201 is to be transmitted to radial rib 27 by housing 29 and further to be transmitted to air breathing engine inlet shell 24 by the heat with polyphase windings 23, and the artificial convection of compressor moving air that suck and that around nappe 240, flow, also can pass through hole and gap in the nappe 240, or the like.The cooling of the whole synchronous machine 2 also radial passage 31 in the anterior hollow space of the wheel 15 by radial compressor supports, along the direction from the stator 201 of synchronous machine 2 to rotor 200 back of synchronous machine 2.
In not shown design implementation example, the stator 201 of synchronous machine 2 can be made by different suitable modes with rotor 200, and they also can be integrated on the structure of air breathing engine rotating part and standing part by different suitable modes.
For light, synchronous machine 2 is as driver.After air breathing engine starting, expanding when fuel and air burning blows on the turbine bucket, when compressor keeps rotation, synchronous machine 2 can be used as the current generator operation, directly in air breathing engine, use, perhaps also can use for the external equipment of air breathing engine outside, or the like.
The jet engine design of diagram and explanation above the present invention does not limit, the difference that also can structure setting jet according to each type or turbogenerator draws technical solution of the present invention is revised.One of ordinary skill in the art according to technical solution of the present invention and utilize his/her common professional ability, can be applied to technological scheme of the present invention in the suitable special construction.
Commercial Application
Technical solution of the present invention is applied to jet engine, turbogenerator, etc.
Claims (10)
1. one kind comprises radially or the jet or turbogenerator of diagonal angle compressor, compressor has at least one rotating part that rotates in the standing part of jet or turbogenerator, synchronous machine with the stator of mutual collaborative work and rotor is connected at least one rotating part of compressor, it is characterized in that, the rotor (200) of synchronous machine (2) is fixed on the rotating part of the jet or turbogenerator that is connected with compressor, and the stator (201) of the synchronous machine (2) that aligns with the rotor (200) of synchronous machine (2) is contained on the standing part of jet or turbogenerator, and is connected with power supply and/or power device.
2. jet or turbogenerator as claimed in claim 1 is characterized in that, the rotor (200) of synchronous machine (2) is fixed on the rotating part of compressor.
3. jet or turbogenerator as claimed in claim 2 is characterized in that, the rotor (200) of synchronous machine (2) is fixed on the front portion of compressor wheels, and the stator (201) of synchronous machine (2) is fixed on the compressor wheels front.
4. jet or turbogenerator as claimed in claim 3 is characterized in that, the rotor (200) of synchronous machine (2) is contained in the anterior hollow space of compressor wheels.
5. as claim 3 or 4 described jet or turbogenerators, it is characterized in that, the stator (201) of synchronous machine (2) is contained on the nappe (240), nappe is used for the front center that aerodynamics covers compressor wheels, and nappe (240) is fixed on middle part jet or turbogenerator inlet shell (24) by radial rib (27).
6. jet or turbogenerator as claimed in claim 5 is characterized in that, at least one radial rib (27) is a hollow, and as the pipeline of lead (25), lead (25) is used to connect the stator (201) and power supply and/or power device of synchronous machine (2).
7. as claim 5 or 6 described jet or turbogenerators, the stator (201) of synchronous machine (2) is contained on the housing (29) that hangs on nappe (240).
8. as each the described jet or turbogenerator in the claim 1 to 7, it is characterized in that, the rotor (200) of synchronous machine (2) comprises the hollow permanent magnet with even number of poles, and the stator (201) of synchronous machine (2) comprises rotor (200) cavity that is arranged in synchronous machine (2) and the electromagnet with polyphase windings (23), and polyphase windings (23) is connected to power supply and/or power device.
9. as each the described jet or turbogenerator in the claim 1 to 7, it is characterized in that, the rotor (200) of synchronous machine (2) comprises stator (201) cavity that is arranged in synchronous machine (2) and the permanent magnet with even number of poles, and the stator (201) of synchronous machine (2) comprises the have polyphase windings hollow electromagnet of (23), and polyphase windings (23) is connected to power supply and/or power device.
10. as each the described jet or turbogenerator in the claim 1 to 9, it is characterized in that the stator (201) and/or the rotor (200) of synchronous machine (2) are provided with cooling pipe system.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CZ200213449U CZ12724U1 (en) | 2002-09-06 | 2002-09-06 | Jet or turbine engine |
| CZPUV200213449 | 2002-09-06 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1682023A true CN1682023A (en) | 2005-10-12 |
| CN100447388C CN100447388C (en) | 2008-12-31 |
Family
ID=5476593
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB038212609A Expired - Lifetime CN100447388C (en) | 2002-09-06 | 2003-09-03 | Jet motor or turbine motor |
Country Status (4)
| Country | Link |
|---|---|
| CN (1) | CN100447388C (en) |
| AU (1) | AU2003266099A1 (en) |
| CZ (1) | CZ12724U1 (en) |
| WO (1) | WO2004022948A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101280726B (en) * | 2007-04-03 | 2014-06-04 | 通用电气公司 | Power output system and gas turbine assembly including same |
| CN103967535A (en) * | 2013-02-01 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Refrigeration and electricitygeneration integrated device driven by air turbine |
| CN106703993A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN109072710A (en) * | 2016-05-02 | 2018-12-21 | 西门子股份公司 | The drive system with generator for aircraft |
| CN109113803A (en) * | 2018-11-09 | 2019-01-01 | 上海尚实能源科技有限公司 | Rotor startup structure for turbogenerator |
| CN111828375A (en) * | 2020-06-30 | 2020-10-27 | 中国航发南方工业有限公司 | Split-flow centrifugal impeller and aircraft engine with same |
Families Citing this family (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1614855A1 (en) * | 2004-07-05 | 2006-01-11 | Siemens Aktiengesellschaft | Turbomachine and method to operate such a turbomachine |
| EP1825116A2 (en) | 2004-12-01 | 2007-08-29 | United Technologies Corporation | Ejector cooling of outer case for tip turbine engine |
| US7976272B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Inflatable bleed valve for a turbine engine |
| EP1831521B1 (en) | 2004-12-01 | 2008-08-20 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
| EP1831530B1 (en) | 2004-12-01 | 2009-02-25 | United Technologies Corporation | Compressor variable stage remote actuation for turbine engine |
| WO2006059975A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
| EP1841960B1 (en) * | 2004-12-01 | 2011-05-25 | United Technologies Corporation | Starter generator system for a tip turbine engine |
| WO2006059985A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Axial compressor for tip turbine engine |
| EP1825113B1 (en) | 2004-12-01 | 2012-10-24 | United Technologies Corporation | Counter-rotating gearbox for tip turbine engine |
| US8096753B2 (en) | 2004-12-01 | 2012-01-17 | United Technologies Corporation | Tip turbine engine and operating method with reverse core airflow |
| US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
| EP1828574B1 (en) | 2004-12-01 | 2010-11-03 | United Technologies Corporation | Close coupled gearbox assembly for a tip turbine engine |
| EP1825126B1 (en) | 2004-12-01 | 2011-02-16 | United Technologies Corporation | Vectoring transition duct for turbine engine |
| US7883315B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan rotor of a tip turbine engine |
| US8757959B2 (en) | 2004-12-01 | 2014-06-24 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
| WO2006059970A2 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
| WO2006059995A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Gearbox lubrication supply system for a tip turbine engine |
| US8024931B2 (en) | 2004-12-01 | 2011-09-27 | United Technologies Corporation | Combustor for turbine engine |
| EP1828573B1 (en) | 2004-12-01 | 2010-06-16 | United Technologies Corporation | Hydraulic seal for a gearbox of a tip turbine engine |
| US7424805B2 (en) | 2005-04-29 | 2008-09-16 | General Electric Company | Supersonic missile turbojet engine |
| US7448199B2 (en) * | 2005-04-29 | 2008-11-11 | General Electric Company | Self powdered missile turbojet |
| US7509797B2 (en) | 2005-04-29 | 2009-03-31 | General Electric Company | Thrust vectoring missile turbojet |
| US7475545B2 (en) | 2005-04-29 | 2009-01-13 | General Electric Company | Fladed supersonic missile turbojet |
| GB2567674B (en) * | 2017-10-20 | 2022-04-06 | Rolls Royce Plc | Motor Generator System for a Gas Turbine Engine |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3187188A (en) * | 1959-07-21 | 1965-06-01 | Curtiss Wright Corp | High speed turbo-generator |
| US3071691A (en) * | 1960-05-31 | 1963-01-01 | Curtiss Wright Corp | Shaft support |
| GB1041587A (en) * | 1962-08-27 | 1966-09-07 | Bristol Siddeley Engines Ltd | Improvements in gas turbine engines |
| GB1147730A (en) * | 1967-12-19 | 1969-04-02 | Rolls Royce | Improvements in or relating to gas turbine engines |
| US3859785A (en) * | 1973-12-17 | 1975-01-14 | Curtiss Wright Corp | Turbine engine with integral compressor and alternator rotor |
| WO1980002585A1 (en) * | 1979-05-14 | 1980-11-27 | Norbert L Osborn | Turbocharger and adaptations thereof |
| US4482303A (en) * | 1982-01-27 | 1984-11-13 | Ray Acosta | Turbo-compressor apparatus |
| US5237817A (en) * | 1992-02-19 | 1993-08-24 | Sundstrand Corporation | Gas turbine engine having low cost speed reduction drive |
-
2002
- 2002-09-06 CZ CZ200213449U patent/CZ12724U1/en not_active IP Right Cessation
-
2003
- 2003-09-03 WO PCT/CZ2003/000050 patent/WO2004022948A1/en not_active Application Discontinuation
- 2003-09-03 CN CNB038212609A patent/CN100447388C/en not_active Expired - Lifetime
- 2003-09-03 AU AU2003266099A patent/AU2003266099A1/en not_active Abandoned
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101280726B (en) * | 2007-04-03 | 2014-06-04 | 通用电气公司 | Power output system and gas turbine assembly including same |
| CN103967535A (en) * | 2013-02-01 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Refrigeration and electricitygeneration integrated device driven by air turbine |
| CN106703993A (en) * | 2015-11-14 | 2017-05-24 | 熵零股份有限公司 | Engine |
| CN109072710A (en) * | 2016-05-02 | 2018-12-21 | 西门子股份公司 | The drive system with generator for aircraft |
| CN109113803A (en) * | 2018-11-09 | 2019-01-01 | 上海尚实能源科技有限公司 | Rotor startup structure for turbogenerator |
| CN111828375A (en) * | 2020-06-30 | 2020-10-27 | 中国航发南方工业有限公司 | Split-flow centrifugal impeller and aircraft engine with same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100447388C (en) | 2008-12-31 |
| CZ12724U1 (en) | 2002-10-23 |
| WO2004022948A1 (en) | 2004-03-18 |
| AU2003266099A1 (en) | 2004-03-29 |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
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Granted publication date: 20081231 |