CN108868896A - A kind of engine turbine moving blades and turbogenerator - Google Patents
A kind of engine turbine moving blades and turbogenerator Download PDFInfo
- Publication number
- CN108868896A CN108868896A CN201810694911.7A CN201810694911A CN108868896A CN 108868896 A CN108868896 A CN 108868896A CN 201810694911 A CN201810694911 A CN 201810694911A CN 108868896 A CN108868896 A CN 108868896A
- Authority
- CN
- China
- Prior art keywords
- moving blades
- turbo blade
- blade
- engine turbine
- support ring
- 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.)
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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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
- F01D5/14—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
- F01D5/186—Film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of engine turbine moving blades and using the turbogenerator of the moving blades, including including several turbo blades and support ring, the leaf top of the turbo blade is fixed on the inner ring of the support ring.Engine turbine moving blades in present invention extension supporting ring on the basis of turbo blade, the leaf top of turbo blade is fixed on the inner ring of support ring, greatly reduce manufacture and the assembly difficulty of turbine rotor blade grid, save cost of manufacture, the rigidity of turbo blade is enhanced simultaneously, extend the service life of device, it is therefore prevented that flue gas passes through the leakage on movable vane leaf top, improves system effectiveness.
Description
Technical field
The present invention relates to engine turbine technical fields, more particularly to a kind of engine turbine moving blades and propeller for turboprop
Machine.
Background technique
The turbine rotor blade inter-blade channel of turbogenerator is the design channel for airflow, gas should be made complete in principle
Runner between leaf grating is passed through in portion, is possible to so that obtaining ideal efficiency.It, will but in fact, the safety in order to guarantee leaf grating
Certain gap is reserved on the leaf top of movable vane, while in order to guarantee that the leakage rate on leaf top is few as much as possible, also to design other
Some supplementary structures, such as prevent leakage labyrinth structure, complicated marginal texture, this proposes very high to the processing of blade
Requirement；Blade requires manufacture consistency very high, and needs are fine when different blades is mounted in turbine hub is sized,
It is brought a great deal of trouble for assembly work, so that the process for machining and manufacturing of movable vane is complicated, it is at high cost.
Summary of the invention
The object of the present invention is to provide a kind of engine turbine moving blades and using the turbogenerator of the moving blades, with solution
Certainly the above-mentioned problems of the prior art reduces the manufacture of turbine rotor blade grid and assembly difficulty, saves cost of manufacture, enhancing hair
The rigidity of the turbo blade of motivation extends the service life of device.
To achieve the above object, the present invention provides following schemes：
The present invention provides a kind of engine turbine moving blades, including several turbo blades and support ring, the turbines
The leaf top of blade is fixed on the inner ring of the support ring.
Preferably, the outer ring both sides of edges of the support ring is equipped with end seals structure, between the end seals structure
Toroidal cavity formed gas passage chamber, the gas passage chamber be equipped with multiple ventholes.
Preferably, the installation site of the venthole and the turbo blade in the support ring is corresponding.
Preferably, the turbo blade is hollow blade, and the venthole is connected with the hollow cavity of the turbo blade
It is logical, in the hollow cavity for cooling gas to be drained to the turbo blade.
Preferably, the venthole being connected with each turbo blade is at least three.
Preferably, the turbo blade be equipped with aperture, for cooling gas outflow and in the turbine blade surface
Form air film.
Preferably, the blade root of the turbo blade is fixed on axis.
Preferably, the width of the turbo blade is equal with the thickness of the support ring.
A kind of turbogenerator, including engine turbine moving blades described above.
The present invention achieves following technical effect compared with the existing technology：Base of the engine turbine moving blades in turbo blade
The leaf top of turbo blade is fixed on the inner ring of support ring, greatly reduces the system of turbine rotor blade grid by extension supporting ring on plinth
It makes and assembly difficulty, saves cost of manufacture, while enhancing the rigidity of turbo blade, extend the service life of device, additionally it is possible to
It prevents flue gas from passing through the leakage on movable vane leaf top, improves system effectiveness.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the structural schematic diagram of inventive engine turbine rotor blade grid；
Fig. 2 is the structural schematic diagram of support ring of the present invention；
Fig. 3 is the structural schematic diagram of turbo blade of the present invention；
Fig. 4 is the top view of support ring of the present invention；
Fig. 5 is the structural schematic diagram of inventive engine turbine rotor blade grid Section A-A；
Wherein：1- support ring, 2- turbo blade, 11- end seals structure, 12- gas passage chamber, 13- venthole.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art under the premise of not making the creative labor it is obtained it is all its
His embodiment, shall fall within the protection scope of the present invention.
The object of the present invention is to provide a kind of engine turbine moving blades and turbogenerators, to solve prior art presence
The problem of, the manufacture of turbine rotor blade grid and assembly difficulty are reduced, cost of manufacture is saved, enhances the rigid of the turbo blade of engine
Property, extend the service life of device, additionally it is possible to prevent flue gas from passing through the leakage on movable vane leaf top, improve system effectiveness.
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, with reference to the accompanying drawing and specific real
Applying mode, the present invention is described in further detail.
As Figure 1-Figure 5：A kind of engine turbine moving blades are present embodiments provided, 12 turbines are preferably comprised
Blade 2 and a support ring 1, the leaf top of turbo blade 2 are fixed on the inner ring of support ring 1, the width and branch of turbo blade 2
The thickness of pushing out ring 1 is equal, and the blade root of turbo blade 2 is fixed on axis, reduces the manufacture of turbine rotor blade grid and assembly difficulty, section
Cost of manufacture is saved, while enhancing the rigidity of the turbo blade of engine, extends the service life of device.
The outer ring both sides of edges of support ring 1 is equipped with end seals structure 11, the toroidal cavity between end seals structure 11
Gas passage chamber 12 is formed, circumferentially arranged with a circle venthole 13 on gas passage chamber 12, venthole 13 and turbo blade 2 exist
Installation site in support ring 1 is corresponding, and the venthole 13 being connected with each turbo blade 2 is preferably three, turbo blade 2
For hollow blade, venthole 13 is connected with the hollow cavity of turbo blade 2, and turbo blade 2 is equipped with aperture.For air film
Cooling turbine rotor blade grid, the high pressure low temperature gas by draining compressor are drained to gas passage chamber 12 by venthole 13
Enter the hollow blade of turbo blade 2, then forms air film by the aperture outflow on turbo blade 2 and on 2 surface of turbo blade, it is cold
But with protection moving blades, meanwhile, the high pressure gas of introducing can also prevent flue gas from leaking by the leaf tops of turbine rotor blade grid.
For moving blades, no matter high pressure low temperature gas guided into blade root or leaf top, introduced high pressure low temperature gas
Derive from compressor.If introduced from blade root, the channel of air-flow is to introduce leaf grating from axle portion, is built into cooling in axis
Air duct, it is inherently extremely difficult, also to guarantee certain ventilation quantity and the alap pressure loss, difficulty is very
Height, production difficulty of processing is big, while can also reduce the intensity of axis.Gaseous film control in the present embodiment is for moving blades
, and high pressure low temperature gas is introduced from leaf top, the channel of air-flow is placed in outside casing, the broad space of outside can be protected
Good ventilation quantity and low pressure drop are demonstrate,proved, and is more easily implemented, even introduces a snorkel, operation side from compressor portion
Just, as long as design is reasonable, so that it may solve the problems, such as that turbine uses the air distribution of gaseous film control.And high pressure low temperature gas is introduced from leaf top
Body, other than being conducive to process and configure, another benefit is that opposite higher-pressure region can be formed in the region Ye Ding, and flue gas is difficult
Downstream to be flowed out by higher-pressure region, also just prevents flue gas from the leakage on leaf top in this way, play the sealing of movable vane.
The present embodiment additionally provides a kind of turbogenerator, applies above-mentioned engine turbine moving blades, has above-mentioned hair
The turbogenerator of motivation turbine rotor blade grid also has above-mentioned all technical effects.
Apply that a specific example illustrates the principle and implementation of the invention in this specification, above embodiments
Explanation be merely used to help understand method and its core concept of the invention；At the same time, for those skilled in the art,
According to the thought of the present invention, there will be changes in the specific implementation manner and application range.In conclusion in this specification
Appearance should not be construed as limiting the invention.
Claims (9)
1. a kind of engine turbine moving blades, it is characterised in that：Including several turbo blades and support ring, the turbo blade
Leaf top be fixed on the inner ring of the support ring.
2. engine turbine moving blades according to claim 1, it is characterised in that：The outer ring both sides of edges of the support ring
Equipped with end seals structure, the toroidal cavity between the end seals structure forms gas passage chamber, the gas passage chamber
It is equipped with multiple ventholes.
3. engine turbine moving blades according to claim 2, it is characterised in that：The venthole and the turbo blade
Installation site in the support ring is corresponding.
4. engine turbine moving blades according to claim 3, it is characterised in that：The turbo blade is hollow blade,
The venthole is connected with the hollow cavity of the turbo blade, for draining cooling gas in the turbo blade
In cavity body.
5. engine turbine moving blades according to claim 4, it is characterised in that：It is connected with each turbo blade
The venthole be at least three.
6. engine turbine moving blades according to claim 4, it is characterised in that：The turbo blade is equipped with aperture,
For cooling gas outflow and the turbine blade surface formed air film.
7. engine turbine moving blades according to claim 1, it is characterised in that：The blade root of the turbo blade is fixed on
On axis.
8. engine turbine moving blades according to claim 1, it is characterised in that：The width of the turbo blade with it is described
The thickness of support ring is equal.
9. a kind of turbogenerator, which is characterized in that including engine turbine movable vane such as of any of claims 1-8
Grid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810694911.7A CN108868896A (en) | 2018-06-29 | 2018-06-29 | A kind of engine turbine moving blades and turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810694911.7A CN108868896A (en) | 2018-06-29 | 2018-06-29 | A kind of engine turbine moving blades and turbogenerator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108868896A true CN108868896A (en) | 2018-11-23 |
Family
ID=64296929
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810694911.7A Pending CN108868896A (en) | 2018-06-29 | 2018-06-29 | A kind of engine turbine moving blades and turbogenerator |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4747900A (en) * | 1984-07-07 | 1988-05-31 | Rolls-Royce Plc | Method of manufacture of compressor rotor assembly |
| US5488825A (en) * | 1994-10-31 | 1996-02-06 | Westinghouse Electric Corporation | Gas turbine vane with enhanced cooling |
| CN103670529A (en) * | 2012-09-26 | 2014-03-26 | 阿尔斯通技术有限公司 | Method and cooling system for cooling blades of at least one blade row |
| CN103967533A (en) * | 2014-04-17 | 2014-08-06 | 无锡蠡湖叶轮制造有限公司 | Turbine for turbine engine |
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
| CN104847417A (en) * | 2014-02-14 | 2015-08-19 | 杨士恒 | Plane linear integral blade |
| DE102014203871A1 (en) * | 2014-03-04 | 2015-09-10 | Robert Bosch Gmbh | Impeller for a turbine |
-
2018
- 2018-06-29 CN CN201810694911.7A patent/CN108868896A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4747900A (en) * | 1984-07-07 | 1988-05-31 | Rolls-Royce Plc | Method of manufacture of compressor rotor assembly |
| US5488825A (en) * | 1994-10-31 | 1996-02-06 | Westinghouse Electric Corporation | Gas turbine vane with enhanced cooling |
| CN103670529A (en) * | 2012-09-26 | 2014-03-26 | 阿尔斯通技术有限公司 | Method and cooling system for cooling blades of at least one blade row |
| CN104847417A (en) * | 2014-02-14 | 2015-08-19 | 杨士恒 | Plane linear integral blade |
| DE102014203871A1 (en) * | 2014-03-04 | 2015-09-10 | Robert Bosch Gmbh | Impeller for a turbine |
| CN103967533A (en) * | 2014-04-17 | 2014-08-06 | 无锡蠡湖叶轮制造有限公司 | Turbine for turbine engine |
| CN104454026A (en) * | 2014-11-09 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Zigzag-shroud of aero-engine rotor vane |
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Application publication date: 20181123 |
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