CN106593542A - Amphibious relay turbine engine - Google Patents
Amphibious relay turbine engine Download PDFInfo
- Publication number
- CN106593542A CN106593542A CN201611053790.5A CN201611053790A CN106593542A CN 106593542 A CN106593542 A CN 106593542A CN 201611053790 A CN201611053790 A CN 201611053790A CN 106593542 A CN106593542 A CN 106593542A
- Authority
- CN
- China
- Prior art keywords
- amphibious
- relay
- turbogenerator
- engine
- turbine
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an amphibious relay turbine engine. The amphibious relay turbine engine comprises an engine control module. The engine control module comprises a control interface. The control interface can be switched into an aero-engine control mode or a ground gas turbine control mode; and turbine blades and a combustion chamber of the amphibious relay turbine engine are manufactured by adopting an additional material design and manufacture technology. The amphibious relay turbine engine provided by the invention has the beneficial effects that the amphibious relay turbine engine takes the surplus value of the engine after retirement of an aerospace craft into consideration. By adoption of an advanced technology and a unique service mode, the comprehensive service life of the gas turbine is extremely prolonged, and the comprehensive cost of the engine is lowered.
Description
Technical field
The present invention relates to technical field of engines, more particularly to amphibious relay turbogenerator.
Background technology
At present, the whole world is aiming at aviation without any a gas turbine at the beginning of design（Life-span early stage）And ground
（Later stage in life-span）Amphibious application and develop.Current almost all of aero-engine is reaching the upper of Flight Design service life
It is i.e. retired after limit to scrap, really it is a kind of wave for a aero-engine for having put into huge manpower and materials research and development manufacture
Take.The technical requirements of the superelevation of aero-engine often also have larger residual life after causing its retired, through diagnosis and repair
Can further using being ground gas turbine, such as distributed power station, ship power, natural gas line conveying compressor etc..And incite somebody to action
A aero-engine is successfully improved to that type success is reliable, efficient gas turbine need for huge science research input and compared with
The long R＆D cycle.
The content of the invention
The invention provides a kind of amphibious relay turbogenerator, including engine control module, the electromotor control
Module includes control interface, and the control interface can be cut between aero-engine and ground gas turbine control model
Change, the turbo blade of amphibious relay turbogenerator and combustor are manufactured using material design and manufacturing technology is increased.
As a further improvement on the present invention, the amphibious relay turbogenerator is provided with the fixed strong point, with easily
Fixation when face uses.
As a further improvement on the present invention, increasing material design and manufacturing technology is included using the sub-surface fine-structure mesh based on ball unit
Structure design.
As a further improvement on the present invention, turbo blade is using the increasing material design based on hollow ball unit and manufacturing technology
Produce Turbine Blades With temperature.
As a further improvement on the present invention, the material that increases of combustor manufactures and designs, and fuel is directly set with the runner of air
Meter is produced in the cavity of combustor.
As a further improvement on the present invention, the rotor supports of amphibious relay turbogenerator adopt long-life bearing skill
Art.
As a further improvement on the present invention, long-life bearing technology is included using magnetic suspension bearing technology, it is ensured that rotor
It is contactless between support zone and bearing during high speed operation.
As a further improvement on the present invention, the material of the amphibious relay turbogenerator adopts corrosion-and high-temp-resistant material
Material.
As a further improvement on the present invention, the amphibious relay turbogenerator is provided with mounting hole site and lifting hole position.
As a further improvement on the present invention, the amphibious relay turbogenerator also includes monitoring module, the monitoring mould
Block is used to gather the parameter of amphibious relay turbogenerator, and the monitoring module is used to enter row data communication with high in the clouds.
The invention has the beneficial effects as follows：The amphibious gas turbine of the present invention, takes into full account electromotor from aerospace craft
The surplus value after retired, using advanced technology and the service mode of uniqueness, can greatly increase the comprehensive longevity of gas turbine
Life, reduces the integrated cost of electromotor.
Description of the drawings
Fig. 1 is the structural representation of the present invention.
Specific embodiment
As shown in figure 1, the invention discloses a kind of amphibious relay turbogenerator, including engine control module, it is described
Engine control module includes control interface, and the control interface can be in aero-engine and ground gas turbine control model
Between switch over, the turbo blade of amphibious relay turbogenerator and combustor are manufactured using material design and manufacturing technology is increased.
Control module adopts open modularity, standardization, seriation, Design of digital.
Modularity, standardization, seriation, digitized control module can easily aero-engine control model and ground
Switch between the gas turbine control model of face, without the need for carrying out extra repacking.
Control module is specifically included and backs up a set of modularity, standardization, digitized control interface for Throttle Opening Control etc., can
Easily switch between aero-engine and ground gas turbine control model, without the need for repacking electromotor space flight can be met
Control with Ground Application is required.
Modularity mainly enters the part such as velocity pick-up and oil circuit control, lubrication monitoring, pressure and temperature sensing control
Row modularized design；Standardization is mainly backed up all soft and hardware interfaces related with control mode switch by international standard,
Aspect pattern can be switched fast when changing；Seriation is mainly the chip of control section, the scope of controllable parameter, controlling interface
Language etc. is all serial optional；It is digitized that digitized is mainly the input and output of all control modules.
The amphibious relay turbogenerator is provided with the fixed strong point, to facilitate fixation when ground uses, takes into full account
The huge difference of the condition that aircraft and ground are fixed, so the strong point of this reserved fixation is also to be even more important.
Increasing material design and manufacturing technology includes being designed using the sub-surface fine mesh structure based on ball unit, thoroughly solves current boat
The problem that empty engine thermal end pieces manufacture difficulty is big, radiating is difficult.
Turbo blade is no longer needed with traditional complicated moulding process, and turbo blade is using the increasing based on hollow ball unit
Material is designed and manufacturing technology manufacture mass lighter, the more preferable Turbine Blades With temperature of intensity.
The material that increases of combustor manufactures and designs, and the runner of fuel and air is directly designed and produced in the cavity of combustor,
Radiating linkage work is supplied and cooled down to fuel, without the need for increasing extra cooling and radiating module.
The rotor supports of amphibious relay turbogenerator adopt long-life bearing technology.
Long-life bearing technology is included using magnetic suspension bearing technology, it is ensured that during rotor high speed operation, support zone and axle
It is contactless between holding, overcoming traditional ball bearing and ball bearing can only put when load is born contact or linear contact lay
Feature.
The material of the amphibious relay turbogenerator adopts corrosion-and high-temp-resistant material, can not only face the high temperature of combustor
High pressure, moreover it is possible to tackle it is retired after etching problem when the high salinity environments such as naval vessel are used.
The present invention just takes into full account that it is applied to ground combustion after retired from aerospace craft at the beginning of the design of electromotor
The probability of gas-turbine, specifically can be applicable to including but not limited to distributed power station, ship power and natural gas line delivery pressure
The aspects such as mechanism of qi.
The present invention makes fuel quick between aerial kerosene and natural gas in structure using efficiently piping foundation technology
Conversion.
In method of service, the amphibious relay turbogenerator of the present invention successively serves Aero-Space in the way of leasing
And land equipment, all the time in the monitoring state in high in the clouds, user uses by all means, amphibious relay whirlpool for health status and ruuning situation
The operation conditions monitoring of turbine and maintenance and repair whole process are not required to user's participation.
The amphibious relay turbogenerator military service early stage of the present invention plays a role as aero-engine, waits in terms of aviation
End Of Service is return behind ground, then can easily be replaced by power turbine output power.
The amphibious relay turbogenerator of the present invention includes but is not limited in structure the structure of whirlpool axle and turbo oar engine
Form.
The multi-functional combustion system of the present invention, need to only carry out the replacing and some other slight repacking of oil line pipe just
Applicable various common fuels.
The amphibious relay turbogenerator of the present invention is whole under the monitor state of high in the clouds, all service datas and each part
Residual life have good grounds all the time.
It is an object of the invention to change the retired present situation scrapped of aero-engine, develop a amphibious relay turbine and send out
Motivation, fully play electromotor it is retired from aerospace craft after the surplus value.The amphibious gas turbine is at the beginning of design
Just take into full account that electromotor is adapted as gas turbine and is continuing with ground and naval vessel after retired from aerospace craft
Possibility, some positions using compatible aero-engine and gas turbine device, removable connecing is reserved at some positions
Mouthful, using color design and manufacturing technology is increased, some parts can be general under various use patterns for some parts.
The changeable type turbine of present invention design is played in the early stage that amphibious gas turbine is on active service as common turbine to be made
With then being easily replaced by power turbine output shaft until it returns ground service as aero-engine End Of Service
To power.
The present invention adopts switchable pipe-line system, realizes multi-functional（Pluralities of fuel）Burning.
The amphibious relay turbogenerator is provided with mounting hole site and lifting hole position, and mounting hole site is used for the amphibious relay turbine
Electromotor is arranged on specified location, and lifting hole position is used to be used when lifting the amphibious relay turbogenerator.
The amphibious relay turbogenerator also includes monitoring module, and the monitoring module is used to gather amphibious relay turbine
Motivation adopts number, and the monitoring module is used to enter row data communication with high in the clouds.
The present invention amphibious gas turbine, take into full account electromotor it is retired from aerospace craft after the surplus value, adopt
With advanced technology and the service mode of uniqueness, can greatly increase the comprehensive life of gas turbine, reduce the synthesis of electromotor
Cost.
Above content is to combine specific preferred implementation further description made for the present invention, it is impossible to assert
The present invention be embodied as be confined to these explanations.For general technical staff of the technical field of the invention,
On the premise of without departing from present inventive concept, some simple deduction or replace can also be made, should all be considered as belonging to the present invention's
Protection domain.
Claims (10)
1. a kind of amphibious relay turbogenerator, it is characterised in that including engine control module, the engine control module
Including control interface, the control interface can be switched between aero-engine and ground gas turbine control model, and two
Dwell relay turbogenerator turbo blade and combustor using increase material design and manufacturing technology manufactured.
2. amphibious relay turbogenerator according to claim 1, it is characterised in that the amphibious relay turbogenerator sets
There is the fixed strong point, to facilitate fixation when ground uses.
3. amphibious relay turbogenerator according to claim 1, it is characterised in that increasing material design and manufacturing technology includes adopting
Designed with the sub-surface fine mesh structure based on ball unit.
4. amphibious relay turbogenerator according to claim 1, it is characterised in that turbo blade is using being based on hollow ball
The increasing material design of unit produces Turbine Blades With temperature with manufacturing technology.
5. amphibious relay turbogenerator according to claim 1, it is characterised in that the increasing material of combustor manufactures and designs then
The runner of fuel and air is directly designed and produced in the cavity of combustor.
6. amphibious relay turbogenerator according to claim 1, it is characterised in that amphibious relay turbogenerator turns
Son is supported and adopts long-life bearing technology.
7. amphibious relay turbogenerator according to claim 6, it is characterised in that long-life bearing technology includes adopting
Magnetic suspension bearing technology, it is ensured that during rotor high speed operation, is contactless between support zone and bearing.
8. amphibious relay turbogenerator according to claim 1, it is characterised in that the amphibious relay turbogenerator
Material adopts corrosion-and high-temp-resistant material.
9. amphibious relay turbogenerator according to claim 1, it is characterised in that amphibious turbogenerator is in structure
The including but not limited to version of whirlpool axle and turbo oar engine.
10. amphibious relay turbogenerator according to claim 1, it is characterised in that electromotor is provided with monitoring module,
Aero-Space and land equipment are successively served in the way of leasing, health status and ruuning situation are all the time in the monitoring in high in the clouds
In state, operation conditions monitoring and maintenance and repair whole process are not required to user's participation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611053790.5A CN106593542A (en) | 2016-11-25 | 2016-11-25 | Amphibious relay turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611053790.5A CN106593542A (en) | 2016-11-25 | 2016-11-25 | Amphibious relay turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106593542A true CN106593542A (en) | 2017-04-26 |
Family
ID=58593241
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611053790.5A Pending CN106593542A (en) | 2016-11-25 | 2016-11-25 | Amphibious relay turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106593542A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1055224A (en) * | 1990-03-23 | 1991-10-09 | 北京市西城新开通用试验厂 | With the aircraft engine is the industrial suspended pump of power |
| JP2010254296A (en) * | 2009-04-22 | 2010-11-11 | Hamilton Sundstrand Corp | Distributed electronic engine control system and control method for gas turbine engine |
| CN102116216A (en) * | 2010-12-30 | 2011-07-06 | 董国光 | Hybrid detonation rotor shaft (all-electric) intelligent engine |
| CN102529621A (en) * | 2012-01-13 | 2012-07-04 | 大连理工大学 | Unmanned triphibian vehicle control system and unmanned triphibian vehicle control method |
| CN103277813A (en) * | 2013-05-30 | 2013-09-04 | 北京航空航天大学 | Low-pollution combustor for emission reduction through hydrogenation during aviation fuel combustion |
-
2016
- 2016-11-25 CN CN201611053790.5A patent/CN106593542A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1055224A (en) * | 1990-03-23 | 1991-10-09 | 北京市西城新开通用试验厂 | With the aircraft engine is the industrial suspended pump of power |
| JP2010254296A (en) * | 2009-04-22 | 2010-11-11 | Hamilton Sundstrand Corp | Distributed electronic engine control system and control method for gas turbine engine |
| CN102116216A (en) * | 2010-12-30 | 2011-07-06 | 董国光 | Hybrid detonation rotor shaft (all-electric) intelligent engine |
| CN102529621A (en) * | 2012-01-13 | 2012-07-04 | 大连理工大学 | Unmanned triphibian vehicle control system and unmanned triphibian vehicle control method |
| CN103277813A (en) * | 2013-05-30 | 2013-09-04 | 北京航空航天大学 | Low-pollution combustor for emission reduction through hydrogenation during aviation fuel combustion |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170426 |
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| RJ01 | Rejection of invention patent application after publication |