CN110067774A - The compressor of combined impeller and gas-turbine unit - Google Patents
The compressor of combined impeller and gas-turbine unit Download PDFInfo
- Publication number
- CN110067774A CN110067774A CN201910302200.5A CN201910302200A CN110067774A CN 110067774 A CN110067774 A CN 110067774A CN 201910302200 A CN201910302200 A CN 201910302200A CN 110067774 A CN110067774 A CN 110067774A
- Authority
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- China
- Prior art keywords
- winglet
- rotor blade
- combined impeller
- wheel hub
- combined
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of combined impellers, including wheel hub and the rotor blade radially laid along wheel hub, multiple rotor blades are provided at circumferentially spaced along wheel hub, rotor blade includes pressure face and suction surface, combined impeller further includes the winglet circumferentially laid along combined impeller, winglet is each passed through pressure face and the setting of shown suction surface along the circumferential direction of combined impeller, for inhibiting air-flow spanwise mixing in the airflow channel between adjacent rotor blades and inhibiting the resonance generated between rotor blade.Technical solution of the present invention increases the rigidity of rotor blade by the way that the winglet circumferentially laid along combined impeller is arranged, play the role of damper simultaneously, unsteady aerodynamic force and centrifugal force bring vibrational energy are absorbed, inhibits the vibration of rotor blade, improves the vibration performance of rotor blade；It is each passed through pressure face and suction surface setting by winglet, radial separation is inhibited using the method for physical barrier, inhibits to separate due to spanwise mixing bring air-flow.
Description
Technical field
The present invention relates to impeller machinery technical fields, particularly, are related to a kind of combined impeller.The invention further relates to a kind of combustions
The compressor of gas eddy turbine.
Background technique
Currently, the compressor of gas-turbine unit is mainly used for continuously sucking air from atmosphere and be compressed.For
The number of rotor blades of the continuous performance for promoting fan or compressor, fan or compressor becomes fewer and fewer, this allows for gas
Stream is easier to occur in the rotor blade passage of compressor exhibition to separation；While in order to promote the pneumatic property of fan or compressor
Can, rotor blade thins down, so that vibration of rotor blades characteristic is deteriorated.
Due to depositing in compressor channel (airflow channel between two adjacent rotor blades) on existing compressor
In centrifugal force, there are pressure differences and blending along radial direction for air-flow, especially in the lower situation of compressor rotor blade consistency, gas
It is obvious to flow spanwise mixing, is easy to happen separation, influences the performance of compressor, and the increase of rotor blade consistency will increase and calm the anger
The weight of machine causes loss to increase, reduces the efficiency of compressor；Rotor blade biggish for aspect ratio, especially calms the anger
The earlier stages of machine, vibration characteristics is poor, and under the collective effect of unsteady aerodynamic force and centrifugal force, rotor blade easily occurs altogether
Vibration.
Summary of the invention
The present invention provides a kind of combined impellers, to solve the impeller portion of the compressor in existing gas-turbine unit
The technical issues of dividing, being easy to produce air-flow spanwise mixing and blade resonance.
To achieve the above object, The technical solution adopted by the invention is as follows:
A kind of combined impeller, including wheel hub and the rotor blade radially laid along wheel hub, multiple rotor blades are along wheel hub
It is provided at circumferentially spaced, rotor blade includes pressure face and suction surface, and combined impeller further includes circumferentially laying along combined impeller
Winglet, winglet is each passed through pressure face and the setting of shown suction surface along the circumferential direction of combined impeller, for inhibiting adjacent rotor blades
Between airflow channel in air-flow spanwise mixing and inhibit the resonance that generates between rotor blade.
Further, the blade tip of the winglet on two adjacent rotor blades mutually abuts laying, by two neighboring turn
Airflow channel between blades is separated into upper and lower two channels.
Further, winglet is set to rotor blade also at high 80% position along the short transverse of rotor blade.
Further, rotor blade includes the rotor blade leading edge and rotor blade trailing edge along axial flow direction laying,
Winglet includes the small nose of wing and winglet trailing edge laid along axial flow direction, and small nose of wing and winglet trailing edge are in rotor leaf
Region between piece leading edge and rotor blade trailing edge.
Further, winglet further includes the winglet lower wall surface close to wheel hub and the winglet upper wall surface far from wheel hub, on winglet
Wall surface is convex surface, concave surface or plane；Winglet lower wall surface is convex surface, concave surface or plane.
Further, the root of rotor blade passes through welding manner, tenon connection type or fir tree connection type and wheel
Hub is detachably connected.
Further, the junction of winglet and rotor blade is equipped with reinforcing rib, and reinforcing rib ring is laid around winglet.
Further, winglet and rotor blade are integrally formed ground casting.
Further, the shape of winglet is arc, and winglet is bent towards the direction of wheel hub.
The present invention also provides a kind of compressors of gas-turbine unit, including combinations of the above impeller, further include being set to
The casing of combined impeller periphery.
The invention has the following advantages:
Combined impeller of the invention, by the way that the winglet circumferentially laid along combined impeller is arranged, since winglet is set to rotor
On blade, the lesser rotor blade of the aspect ratio that rotor blade is divided into two tandems increases the rigidity of rotor blade, together
When play the role of damper, absorb unsteady aerodynamic force and centrifugal force bring vibrational energy, inhibit the vibration of rotor blade,
Improve the vibration performance of rotor blade；It is each passed through pressure face and suction surface setting by winglet, for blocking impeller along diameter
To airflow channel to reduce air-flow spanwise mixing, using the flow behavior of air-flow, inhibit radial using the method for physical barrier
Separation prevents the airflow channel of gas turbine compressor by winglet, reduces the blending flowing of air-flow, inhibits due to spanwise mixing
The separation of bring air-flow avoids compressor impaired while to improve the working efficiency of gas-turbine unit, reduction
The operating cost of gas-turbine unit.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the main view of the combined impeller of the preferred embodiment of the present invention；
Fig. 2 is the rearview of the combined impeller of the preferred embodiment of the present invention；
Fig. 3 is the wheel hub of the preferred embodiment of the present invention and the structural schematic diagram that rotor blade is connect；
Fig. 4 is the rotor blade of the preferred embodiment of the present invention and the structural schematic diagram that winglet is connect；
Fig. 5 is the rotor blade of second embodiment of the invention and the structural schematic diagram that winglet is connect:
Fig. 6 is the structural schematic diagram of winglet installation site；
Air-flow fluidal texture schematic diagram when Fig. 7 is the impeller work of no winglet；
Air-flow fluidal texture schematic diagram when Fig. 8 is the impeller work for being mounted with winglet.
Marginal data:
100, combined impeller；10, wheel hub；20, rotor blade；21, pressure face；22, suction surface；23, rotor blade leading edge；
24, rotor blade trailing edge；30, winglet；31, small nose of wing；32, winglet trailing edge；33, winglet upper wall surface；34, winglet lower wall surface；
40, reinforcing rib；50, casing；200, the compressor of gas-turbine unit.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be limited by following and
The multitude of different ways of covering is implemented.
Fig. 1 is the main view of the combined impeller of the preferred embodiment of the present invention；Fig. 2 is the group hinge of the preferred embodiment of the present invention
The rearview of wheel；Fig. 3 is the wheel hub of the preferred embodiment of the present invention and the structural schematic diagram that rotor blade is connect；Fig. 4 is the present invention
The structural schematic diagram that the rotor blade of preferred embodiment is connect with winglet；Fig. 5 be second embodiment of the invention rotor blade with
The structural schematic diagram of winglet connection；Fig. 6 is the structural schematic diagram of winglet installation site；Gas when Fig. 7 is the impeller work of no winglet
Flow fluidal texture schematic diagram；Air-flow fluidal texture schematic diagram when Fig. 8 is the impeller work for being mounted with winglet.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5 and Fig. 6, combined impeller 100 provided in this embodiment, including wheel hub 10
With the rotor blade 20 radially laid along wheel hub 10, multiple being provided at circumferentially spaced along wheel hub 10 of rotor blade 20, rotor blade
20 include pressure face 21 and suction surface 22, and combined impeller further includes the winglet 30 circumferentially laid along combined impeller, 30 edge of winglet
The circumferential direction of combined impeller is each passed through pressure face 21 and shown suction surface 22 is arranged, for inhibiting between adjacent rotor blades 20
The resonance generated between air-flow spanwise mixing and inhibition rotor blade 20 in airflow channel.
Combined impeller 100 of the invention, by the way that the winglet 30 circumferentially laid along combined impeller 100 is arranged, due to winglet
30 are set on rotor blade 20, and the lesser rotor blade 20 of the aspect ratio that rotor blade 20 is divided into two tandems increases
The rigidity of rotor blade 20, while playing the role of damper, unsteady aerodynamic force and centrifugal force bring vibrational energy are absorbed,
The vibration for inhibiting rotor blade 20, improves the vibration performance of rotor blade 20；21 He of pressure face is each passed through by winglet 30
Suction surface 22 is arranged, special using the flowing of air-flow for blocking the airflow channel of impeller radially to reduce air-flow spanwise mixing
Property, radial separation is inhibited using the method for physical barrier, the airflow channel of gas turbine compressor is prevented by winglet 30, is reduced
The blending of air-flow is flowed, and is inhibited to separate due to spanwise mixing bring air-flow, is avoided compressor impaired while to improve
The working efficiency of gas-turbine unit, reduces the operating cost of gas-turbine unit.
It is to be appreciated that combined impeller 100 of the invention is used in gas-turbine unit, 20 first side of rotor blade
Surface invaginates to form concave pressure face 21, and the surface of 20 second side of rotor blade extends outward to form the suction surface 22 of protrusion.It is small
The wing 30 is each passed through pressure face 21 along the circumferential direction of combined impeller 100 or wheel hub 10 and shown suction surface 22 is arranged, for inhibiting phase
Air-flow spanwise mixing and the resonance generated between rotor blade 20 always in airflow channel between adjacent rotor blade 20, can be with
It is, it, will between airflow channel of the winglet 30 in the formation of two neighboring rotor blade 20 in the circumferential direction of combined impeller 100
The airflow channel formed between two neighboring rotor blade 20 is separated into upper and lower two channels, or the two neighboring rotor of covering
The partial region of the airflow channel formed between blade 20, the airflow channel between two neighboring rotor blade 20 is still connection
's.Specifically, the airflow channel between two neighboring rotor blade 20 is separated into upper and lower two parts by winglet 30, for hindering
Only air-flow is along radial direction spanwise mixing；It is also possible to winglet 30 and only occupies part area between two neighboring rotor blade 20
Domain, and the channel between two neighboring rotor blade 20 is still upper and lower connection, for preventing air-flow from opening up along radial direction to mixing
It is mixed.
Further, the blade tip of the winglet 30 on two adjacent rotor blades 20 mutually abuts laying, by adjacent two
Airflow channel between a rotor blade 20 is separated into upper and lower two channels.Multiple winglets 30 form one around the setting of wheel hub 10
A hoop, for preventing air-flow along radial direction spanwise mixing, the airflow channel that maximum can be limited ground resistance and stop combined impeller 100
Interior air-flow separation.
Further, winglet 30 is set to the axial centre position of rotor blade 20.Using the flow behavior of air-flow, by winglet
30 are set to the axial centre position of rotor blade 20, inhibit radial separation to the maximum extent using the method for physical barrier, also,
Set on the axial centre position of rotor blade 20, in 20 quick rotation of rotor blade, the rigidity of rotor blade 20 is improved, is inhibited
The vibration of rotor blade 20.It is to be appreciated that winglet 30 can also be set to rotor blade 20 far from wheel hub 10 according to the actual situation
One end or set on rotor blade 20 close to one end of wheel hub 10.
More preferably, winglet 30 is set to side of the rotor blade 20 far from wheel hub 10.Height of the winglet 30 along rotor blade 20
Direction is set at 80% high position of 20 leaf of rotor blade.Specifically, winglet 30 is set to along the width direction of rotor blade 20 and turns
At the position 40%-60% in 20 chord length direction of blades；Winglet 30 is set to rotor blade 20 along the short transverse of rotor blade 20
At the high position 40%-80% of leaf.
Further, rotor blade 20 includes the rotor blade leading edge 23 laid along axial flow direction and rotor blade tail
Edge 24, winglet 30 includes the small nose of wing 31 and small nose of wing 32 laid along axial flow direction, before small nose of wing 31 and winglet
Edge 32 is in the region between rotor blade leading edge 23 and rotor blade trailing edge 24.Small nose of wing 31 and small nose of wing 32 is equal
Region between rotor blade leading edge 23 and rotor blade trailing edge 24, can be, and small nose of wing 31 and winglet trailing edge 32 exist
Axial flow direction, which is in, covers entire blade inlet edge 4 to 5 region of blade trailing edge；It is also possible to small nose of wing 31 and winglet trailing edge
32 only cover the partial region that blade inlet edge 4 arrives blade trailing edge 5 in axial flow direction, but without departing from blade inlet edge 4 and blade
The on-bladed region of trailing edge 5.Specifically, prevent small nose of wing 31 beyond rotor blade leading edge 23 without rotor blade 20 region and
Prevent winglet trailing edge 32 from, without 20 region of rotor blade, avoiding the stress at work of rotor blade 20 beyond rotor blade trailing edge 24
Excessive damage.Specifically, in the present embodiment, small nose of wing 31 and rotor blade leading edge 23 are overlappingly arranged, before winglet
Edge 32 and rotor blade trailing edge 24 are overlappingly arranged.
Further, winglet 30 further includes the winglet lower wall surface 34 close to wheel hub 10 and the winglet upper wall surface far from wheel hub 10
33, winglet upper wall surface 33 is convex surface, concave surface or plane；Winglet lower wall surface 34 is convex surface, concave surface or plane.It is to be appreciated that small
Nose of wing 31 and small nose of wing 32 are enclosed the winglet lower wall surface 34 close to wheel hub 10 and the winglet upper wall surface far from wheel hub 10
33.Specifically, in the present embodiment, winglet upper wall surface 33 is convex surface, and winglet lower wall surface 34 is convex surface, to make small nose of wing 31
Cross section shape be ellipse.Pneumatic property when winglet 30 is flowed with rotor blade 20 is increased, winglet 30 is increased
Rigidity, to prevent winglet 30 with damage when 20 high-speed rotation of rotor blade.
Further, the root of rotor blade 20 by welding manner, tenon connection type or fir tree connection type with
Wheel hub 10 is detachably connected.When rotor blade 20 and winglet pass through tenon connection type or fir tree connection type, favorably
In individually maintenance and the replacement of rotor blade 20 and wheel hub 10, it is possible to understand that ground, rotor blade 20 and wheel hub 10 are also possible to one
It casts body formedly,
Further, the junction of winglet 30 and rotor blade 20 is equipped with reinforcing rib 40, and reinforcing rib 40 is around 30 cloth of winglet
If.By the way that reinforcing rib 40 is arranged, when rotor blade 20 aspect ratio itself is larger, further improve rotor blade rigidity and
Aeroperformance.It is cast with being integrally formed it is to be appreciated that can be winglet 30 with rotor blade 20, at this time winglet 30 and main rotor
Blade 20 is a kind of material, and rotor blade 20 processes together with winglet 30, and winglet 30 and 20 junction of rotor blade exist
The reinforcing rib 40 of rounding.Winglet 30 and rotor blade 20 are other than processing technology, without additional technique, simple process.It can also
To be that winglet 30 is processed with main rotor blades 20 respectively, material can be different both at this time, be equipped in main rotor blades 20 with it is small
Aperture similar in 30 aerofoil profile of the wing, every section of winglet 30 pass through the aperture in main rotor blades 20, the company of winglet 30 and rotor blade 20
Place is met using welding or joinery and its construction connection.The winglet 30 Yu rotor blade 20 of separate machined in this way are conducive to rotor blade
20 and winglet 30 individually safeguarded, maintenance cost can be substantially reduced.
Further, the shape of winglet 30 is arc, and winglet 30 is bent towards the direction of wheel hub 10.Multiple formation of winglet 30
One hoop, increases the aeroperformance of rotor blade 20.
The present invention also provides a kind of compressors 200 of gas-turbine unit, including combinations of the above impeller 100, also wrap
Include the casing 50 for being set to 100 periphery of combined impeller.
Please refer to Fig. 7 and Fig. 8, arrow is air-flow in Fig. 7 and Fig. 8, can observe winglet bring flow field change, no winglet
Impeller air-flow flowing, at blade tip position there are obvious swirl flow, the exhibition of air-flow is obvious to separation flowing；There is the leaf of winglet
The flowing of air-flow is taken turns, air-flow is dynamic close to winglet-type surface current, and the exhibition of air-flow is obviously inhibited to separation flowing, while the whirlpool of blade tip
Vortex is dynamic to be eliminated.
Specific embodiment is as follows:
Referring again to Fig. 1, rotor blade 20 is mounted on wheel hub 10, and there are gap, winglets 30 with 50 face of casing for blade tip
It is mounted on 20 pressure face 21 of rotor blade and suction surface 22.The winglet 30 and next rotor leaf grown since pressure face 21
The winglet 30 grown between the suction surface 22 of piece 20 may exist gap, can also extend directly to next rotor blade 20
The winglet 30 that grows of suction surface 22 on, at this point, entire winglet 30 forms a hoop；What is grown since suction surface 22 is small
The wing 30 is identical as the winglet 30 that pressure face 21 starts growth, can deposit between the pressure face 21 of next rotor blade 20
It in gap, can also extend directly on the winglet 30 that the pressure face 21 of next rotor blade 20 is grown, at this point, entire small
The wing 30 forms a hoop.
Rotor blade 20 and winglet 30 are formed by a series of aerofoil sections product is folded, and aerofoil profile is according to conventional shaft circulation cotyledon
20 design method of piece obtains, the specific steps are as follows:
A, it first using the method for numerical simulation or experiment measurement, obtains and meets the outer of performance requirement rotor blade 20
Shape；
B, using the method for numerical simulation or experiment measurement, the shape for meeting performance requirement winglet 30 is obtained；
C, modular rotor blade 20 and winglet 30, using the method for numerical simulation or experiment measurement, judgement takes winglet
Whether the rotor blade 20 after 30 meets performance requirement, next step step is carried out if met, if conditions are not met, return step a；
D, 30 aerofoil profile of output rotor blade 20 and winglet.
The compressor 200 of gas-turbine unit the utility model has the advantages that
1, compared with routine is without the rotor blade 20 of winglet 30, this compressor with winglet 30 can reduce rotor leaf
The quantity of piece 20 reduces by 20 consistency of rotor blade；Meanwhile can reduce the thickness of rotor blade 20 to a certain extent, it improves
The efficiency of fan or compressor；In addition, improving work with gap can be increased after winglet 30 in a certain range without losing performance
Make safety.
2, numerical simulation shows that the present invention can improve the pneumatic efficiency of fan or compressor；
Intensity, vibration calculating show that vibration frequency nargin increases.
3, by the method for physical barrier, the exhibition Xiang Liudong of air-flow is prevented, to inhibit the exhibition of air-flow to separation, improves stream
Dynamic characteristic improves the efficiency and nargin of fan or compressor；In addition winglet 30 divides the biggish rotor blade 20 of aspect ratio itself
At the lesser rotor blade 20 of the aspect ratio of two tandems, to increase the rigidity of rotor blade 20, while winglet 30 can be with
Play the role of damper, unsteady aerodynamic force and centrifugal force bring vibrational energy can be absorbed, so as to improve rotor blade
20 vibration performance.
These are only the preferred embodiment of the present invention, is not intended to restrict the invention, for those skilled in the art
For member, the invention may be variously modified and varied.All within the spirits and principles of the present invention, it is made it is any modification,
Equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of combined impeller, including wheel hub (10) and the rotor blade (20) radially laid along wheel hub (10), multiple described turns
Blades (20) being provided at circumferentially spaced along the wheel hub (10), the rotor blade (20) include pressure face (21) and suction surface
(22), which is characterized in that
The combined impeller further includes the winglet (30) circumferentially laid along the combined impeller, and the winglet (30) is along described group
The circumferential direction of hinge wheel is each passed through the pressure face (21) and shown suction surface (22) setting, for inhibiting the adjacent rotor leaf
The resonance generated between air-flow spanwise mixing and the inhibition rotor blade (20) in airflow channel between piece (20).
2. combined impeller according to claim 1, which is characterized in that
The blade tip of the winglet (30) on the rotor blade (20) of adjacent two mutually abuts laying, will be two neighboring
Airflow channel between the rotor blade (20) is separated into upper and lower two channels.
3. combined impeller according to claim 2, which is characterized in that
The winglet (30) is set to high 80% of the rotor blade (20) leaf along the short transverse of the rotor blade (20)
Set place.
4. combined impeller according to claim 3, which is characterized in that
The rotor blade (20) includes the rotor blade leading edge (23) laid along axial flow direction and rotor blade trailing edge
(24), the winglet (30) includes the small nose of wing (31) and winglet trailing edge (32) laid along axial flow direction, the winglet
Leading edge (31) and the winglet trailing edge (32) be in the rotor blade leading edge (23) and the rotor blade trailing edge (24) it
Between region.
5. combined impeller according to claim 4, which is characterized in that
The winglet (30) further includes small close to the winglet lower wall surface (34) of the wheel hub (10) and far from the wheel hub (10)
Wing upper wall surface (33), the winglet upper wall surface (33) are convex surface, concave surface or plane；The winglet lower wall surface (34) is convex surface, recessed
Face or plane.
6. combined impeller according to claim 5, which is characterized in that
The root of the rotor blade (20) passes through welding manner, tenon connection type or fir tree connection type and the wheel hub
(10) detachably connected.
7. combined impeller according to claim 6, which is characterized in that
The junction of the winglet (30) and the rotor blade (20) is equipped with reinforcing rib (40), and the reinforcing rib (40) is around institute
State winglet (30) laying.
8. combined impeller according to claim 6, which is characterized in that
The winglet (30) and the rotor blade (20) are integrally formed ground casting.
9. combined impeller according to claim 8, which is characterized in that
The shape of the winglet (30) is arc, and the winglet (30) is bent towards the direction of the wheel hub (10).
10. a kind of compressor of gas-turbine unit, which is characterized in that
It further include the casing set on the combined impeller periphery including combined impeller as described in any one of claim 1 to 9
(50)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910302200.5A CN110067774A (en) | 2019-04-16 | 2019-04-16 | The compressor of combined impeller and gas-turbine unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910302200.5A CN110067774A (en) | 2019-04-16 | 2019-04-16 | The compressor of combined impeller and gas-turbine unit |
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| Publication Number | Publication Date |
|---|---|
| CN110067774A true CN110067774A (en) | 2019-07-30 |
Family
ID=67367830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910302200.5A Pending CN110067774A (en) | 2019-04-16 | 2019-04-16 | The compressor of combined impeller and gas-turbine unit |
Country Status (1)
| Country | Link |
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| CN (1) | CN110067774A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983885A (en) * | 2019-12-13 | 2021-06-18 | 通用电气公司 | Shroud for a splitter and rotor airfoil of a fan of a gas turbine engine |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US3193185A (en) * | 1962-10-29 | 1965-07-06 | Gen Electric | Compressor blading |
| US5275531A (en) * | 1993-04-30 | 1994-01-04 | Teleflex, Incorporated | Area ruled fan blade ends for turbofan jet engine |
| CN1500969A (en) * | 2002-11-12 | 2004-06-02 | 通用电气公司 | Method and apparatus for reducing flow across compressor airfoil tips |
| CN101634312A (en) * | 2008-07-23 | 2010-01-27 | 江苏富丽华通用设备有限公司 | Fan blades of axial flow fan |
| CN202152760U (en) * | 2011-07-11 | 2012-02-29 | 张家港施亿百机电设备有限公司 | Axial flow blade |
| CN102691674A (en) * | 2011-03-25 | 2012-09-26 | 台达电子工业股份有限公司 | Impeller structure |
| CN104727858A (en) * | 2013-12-20 | 2015-06-24 | 通用电气公司 | Snubber configurations for turbine rotor blades |
| CN208416618U (en) * | 2017-01-03 | 2019-01-22 | 通用电气公司 | Rotor assembly |
-
2019
- 2019-04-16 CN CN201910302200.5A patent/CN110067774A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US3193185A (en) * | 1962-10-29 | 1965-07-06 | Gen Electric | Compressor blading |
| US5275531A (en) * | 1993-04-30 | 1994-01-04 | Teleflex, Incorporated | Area ruled fan blade ends for turbofan jet engine |
| CN1500969A (en) * | 2002-11-12 | 2004-06-02 | 通用电气公司 | Method and apparatus for reducing flow across compressor airfoil tips |
| CN101634312A (en) * | 2008-07-23 | 2010-01-27 | 江苏富丽华通用设备有限公司 | Fan blades of axial flow fan |
| CN102691674A (en) * | 2011-03-25 | 2012-09-26 | 台达电子工业股份有限公司 | Impeller structure |
| CN202152760U (en) * | 2011-07-11 | 2012-02-29 | 张家港施亿百机电设备有限公司 | Axial flow blade |
| CN104727858A (en) * | 2013-12-20 | 2015-06-24 | 通用电气公司 | Snubber configurations for turbine rotor blades |
| CN208416618U (en) * | 2017-01-03 | 2019-01-22 | 通用电气公司 | Rotor assembly |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112983885A (en) * | 2019-12-13 | 2021-06-18 | 通用电气公司 | Shroud for a splitter and rotor airfoil of a fan of a gas turbine engine |
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Application publication date: 20190730 |
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| RJ01 | Rejection of invention patent application after publication |