CN110094364A - A kind of rotor blade and axial flow compressor - Google Patents
A kind of rotor blade and axial flow compressor Download PDFInfo
- Publication number
- CN110094364A CN110094364A CN201810097806.5A CN201810097806A CN110094364A CN 110094364 A CN110094364 A CN 110094364A CN 201810097806 A CN201810097806 A CN 201810097806A CN 110094364 A CN110094364 A CN 110094364A
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- China
- Prior art keywords
- rotor
- groove
- rotor blade
- blade
- listrium
- 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
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- 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
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- 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
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- 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
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
Abstract
The object of the present invention is to provide a kind of rotor blade and axial flow compressors.Rotor blade is suitably mounted on the rotor drum of the rotor of axial flow compressor, including blade, tenon and listrium；Two be set on rotor drum rotor blade circumferentially adjacent for energy, second groove structure of the pressure face part of the first groove structure and listrium of another rotor blade of the suction surface part of the listrium of one of rotor blade is combined and spliced, to form runner wall surface between two rotor blades of circumferentially adjacent setting, the flow path wall face has circumferentially equably multiple grooves of distribution wave-shaped；Groove extends along the direction of leading edge to trailing edge, and the depth of groove is gradually increased along extending direction；The terminal that groove extends is located in the side wall surface of listrium.The presence of groove reduces the thickness of boundary-layer, and then reduces the blending region of leakage and boundary-layer between grade, thus reduces the caused aerodynamic loss of leakage between grade, improves compressor efficiency and surge margin.
Description
Technical field
The present invention relates to a kind of rotor blade and axial flow compressors.
Background technique
The axial flow compressor of gas turbine includes rotor and stator.Rotor is the combination that a high speed rotation does work to air-flow
Part, for the air work for entering axial flow compressor, rotor to include rotor blade.Stator is connect with casing, including stator leaf
Piece.To avoid high-speed rotating rotor blade and adjacent stator blade touches mill, in the axial direction, the listrium of rotor blade with
There are gap between the listrium of stator blade, which is called Inter-stage gap.Since the import/export of stator blade row exists centainly
Static pressure difference, under the effect of this static pressure difference, the integral shroud of stator blade nearby has air-flow between the grade in the downstream of stator blade
Gap is flowed into via the radial clearance between the integral shroud and rotor drum of stator blade, then from the Inter-stage gap of stator blade upstream
Swim incoming flow, this flowing be called do grade between leak.Requirement with axial flow compressor to performance, grade pressure ratio become higher and higher, lead
Cause the pressure difference between stator leaf row import/export higher and higher, so that leakage is difficult to be obturaged completely between making grade.It is leaked between grade
Air-flow often returned among sprue with the direction for approaching vertical upstream incoming flow, blended with the boundary-layer of upstream incoming flow,
To which biggish loss can be caused.
Therefore, this field needs a kind of preferable rotor blade of structure type, to reduce the attached face of upstream incoming flow as far as possible
The region that leakage blending occurs between layer and grade, and then promote compressor efficiency and surge margin.
Summary of the invention
The purpose of the present invention is to provide a kind of rotor blade, has to leak between the boundary-layer and grade that reduce upstream incoming flow and mix
The mixed region occurred, and then the advantages of raising compressor efficiency and surge margin.
The object of the invention is also to provide a kind of axial flow compressors, including above-mentioned rotor blade, thus have efficiency and
The higher advantage of surge margin.
It for the rotor blade for realizing the purpose, is suitably mounted on the rotor drum of the rotor of axial flow compressor, wraps
Include blade, tenon and listrium；The blade has suction surface and pressure face, and has leading edge and trailing edge along airflow direction；Institute
Stating listrium includes the pressure face part positioned at the suction surface part of the suction surface side and positioned at the pressure face side；It is described
Suction surface part has the first groove structure, and the pressure face part has the second groove structure；
Two be set on the rotor drum the rotor blade circumferentially adjacent for energy, one of them described turn
First groove structure of the suction surface part of the listrium of blades is described with rotor blade described in another
Second groove structure of the pressure face part of listrium is combined and spliced, to turn described in two of circumferentially adjacent setting
Runner wall surface is formed between blades, the flow path wall face has circumferentially equably multiple grooves of distribution wave-shaped；
The groove extends along the runner direction of two rotor blades, and the depth of the groove is along runner direction
It is gradually increased；The terminal that the groove extends is located in the side wall surface of the listrium.
The rotor blade, further feature are that the starting point that the groove extends is apart from one spacing of leading edge
From the depth for the starting point that the groove extends is zero.
The rotor blade, further feature be, the starting point that the groove extends apart from the leading edge 20% to
30% chord length.
The rotor blade, further feature be, the starting point that the depth of the groove extends from the groove is extremely
Terminal gradual change in the form of conic section that the groove extends.
The rotor blade, further feature are that the depth of the groove becomes along extending direction in front half section
The rate of change is less than the rate of second half section variation.
The rotor blade, further feature are that multiple grooves are circumferentially with SIN function or cosine
The form of function is uniformly distributed.
The rotor blade, further feature are, in the circumferential, multiple grooves and two rotor leaves
The position that the blade of piece is separately connected is in crest location.
The rotor blade, further feature be, in the circumferential, all crest locations of multiple grooves with
Original inner flow passage is on same type face, and all wave trough positions are in the lowermost end of multiple grooves.
The rotor blade, further feature are that it is thick that the depth of the groove is less than or equal to the listrium
The half of degree.
The rotor blade, further feature are that the quantity of multiple grooves is 6 to 12.
For the axial flow compressor for realizing the purpose, including casing and the rotor and stator that are set in the casing,
It is characterized in that, the rotor includes rotor drum and rotor blade as described above, and the rotor blade is mounted on the rotor
On drum barrel, and the rotor drum can be followed to rotate.
The axial flow compressor, further feature are that the stator is fixed on the casing；The stator packet
The stator blade along the distribution of airflow direction multistage is included, the stator blade inwardly stretches, and surrounds institute by labyrinth gas seals structure
State rotor drum.
The positive effect of the present invention is that: rotor blade provided by the invention is suitably mounted to axial flow compressor
On the rotor drum of rotor, including blade, tenon and listrium；Listrium includes positioned at the suction surface part of the suction surface side of blade
With the pressure face part for the pressure face side for being located at blade；Suction surface part has the first groove structure, and pressure face part has
Second groove structure；Two be set on rotor drum rotor blade circumferentially adjacent for energy, one of rotor blade
Listrium suction surface part the first groove structure and another rotor blade listrium pressure face part the second groove
Structure is combined and spliced, to form runner wall surface, the flow path wall mask between two rotor blades of circumferentially adjacent setting
There are circumferentially equably multiple grooves of distribution wave-shaped；The runner direction of two rotor blades of groove extends, and groove
Depth is gradually increased along runner direction；The terminal that groove extends is located in the side wall surface of listrium.
Upstream incoming flow can form boundary-layer on the runner wall surface when flowing through runner wall surface.The thickness of the boundary-layer is
It is gradually increased along runner direction.In the inventive solutions, runner wall surface is not flat, but is had circumferentially
Equably multiple grooves of distribution wave-shaped, and the depth of groove is gradually increased along the direction of runner.Therefore, the groove
The boundary-layer can preferably be accommodated.Thus, groove can make the boundary-layer during following rotor drum high-speed rotation
Stronger vortex is generated, and then strengthens the momentum-exchange between boundary-layer and the main flow area of upstream incoming flow, so that upstream
The radially distributed of the flow velocity of the air-flow of the close runner wall surface of incoming flow must be fuller, so that the thickness of boundary-layer is reduced,
And then the blending region of leakage and boundary-layer between grade is reduced, thus the caused aerodynamic loss of leakage between grade is reduced, it improves
Compressor efficiency and surge margin.
Detailed description of the invention
The above and other features of the present invention, property and advantage will pass through retouching with reference to the accompanying drawings and examples
It states and becomes readily apparent from, in which:
Fig. 1 is a part of axis flow air compressor of the present invention along axial sectional view, it is shown that is leaked between grade；
Fig. 2 is the schematic diagram of two rotor blades of circumferentially adjacent setting in the present invention；
Fig. 3 is the schematic diagram for two rotor blades being disposed adjacent in the present invention along airflow direction, it is shown that runner wall surface；
Fig. 4 is the schematic diagram for two rotor blades that inverse airflow direction is disposed adjacent in the present invention, it is shown that runner wall surface；
Fig. 5 is the schematic diagram that region is blended in comparative example, it is shown that biggish blending region；
Fig. 6 is the schematic diagram that region is blended in the present invention, it is shown that lesser blending region；
Fig. 7 is the schematic diagram of boundary-layer in comparative example, it is shown that thicker boundary-layer；
Fig. 8 is the schematic diagram of boundary-layer in the present invention, it is shown that relatively thin boundary-layer.
Specific embodiment
The invention will be further described with attached drawing combined with specific embodiments below, elaborates in the following description more
Details to facilitate a thorough understanding of the present invention, still the present invention obviously can be come with a variety of other ways different from this description it is real
It applies, those skilled in the art can make similar popularization according to practical situations without violating the connotation of the present invention, drill
It unravels silk, therefore should not be limited the scope of the invention with the content of this specific embodiment.
It should be noted that Fig. 1 to Fig. 8 only as an example, its not be according to equal proportion condition draw, and
It should not be construed as limiting in this, as the protection scope to actual requirement of the present invention.
Referring initially to Fig. 1, the axial flow compressor 100 of gas turbine includes rotor and stator.Rotor is a high speed rotation
To the sub-assembly of air-flow acting, for the air work for entering axial flow compressor.Rotor includes rotor drum 1 and along axial more
The rotor blade 2 of grade distribution.Rotor blade 2 includes blade 20, tenon 21 and listrium 22, and fixation is set respectively for blade 20 and tenon 21
It sets in the two sides up and down of listrium 22；Wherein, rotor blade 2 is fixed on rotor drum 1 by tenon 21 and can follow rotor
Drum barrel 1 rotates.Corresponding tongue-and-groove is offered to be cooperatively connected on rotor drum 1 with tenon 21.Blade 20 has 201 He of suction surface
Pressure face 202, and there is leading edge 20a and trailing edge 20b along airflow direction.
With reference to Fig. 2, in the circumferential, the listrium 22 with adjacent two rotor blade 2 of level-one is combined and spliced, adjacent
Two rotor blades 2 between formed runner wall surface C.Specifically, listrium 22 includes the suction face positioned at 201 side of suction surface
Points 221 and positioned at 202 side of pressure face pressure face part 222.Rotor drum 1 is fixed in two adjacent rotor blades 2
After upper, the pressure of the listrium 22 of the suction surface part 221 and another rotor blade 2 of the listrium 22 of one of rotor blade 2
Face part 222 is combined and spliced, to form runner wall surface C.Fig. 2 also shows two combined and spliced seams of listrium 22 5.Upstream is come
Stream F is done work when flowing through runner wall surface C by rotor blade 2, then flows to downstream.Upstream incoming flow F when flowing through runner wall surface C,
Boundary-layer can be formed on runner wall surface C.The principle that boundary-layer is formed can refer to the record of pertinent literature, no longer superfluous herein
It states.
Stator is fixed on the casing 100a of 100 outer radius of axial flow compressor, quiet including being distributed along airflow direction multistage
Blades 3.Stator blade 3 inwardly stretches, and surrounds rotor drum 1 by labyrinth gas seals structure 4.Stator blade 3 is along air-flow side
To the downstream for the rotor blade 2 that same level-one is arranged in.Upstream incoming flow F is rectified diffusion when flowing through stator blade 3.
To avoid touching mill, in the axial direction, rotor between high-speed rotating rotor blade 2 and adjacent stator blade 3
There are gap between the listrium 22 of blade 2 and the listrium 31 of stator blade 3, which is called Inter-stage gap.Due to stator blade 3
There are certain static pressure differences for the import/export of the stator leaf row of composition, and under the effect of this static pressure difference, the integral shroud 30 of stator blade 3 is attached
It closely has between integral shroud 30 and rotor drum 1 of the air-flow f from the Inter-stage gap g1 in the downstream of stator blade 3 via stator blade 3
Radial clearance, then from the Inter-stage gap g2 of 3 upstream of stator blade flow into upstream incoming flow F, this flowing be called do grade between leak.
Requirement with axial flow compressor 100 to performance is higher and higher, and grade pressure ratio also becomes higher and higher, leads to stator leaf
Pressure difference between the import/export of row is higher and higher, so that leakage is difficult to be obturaged completely between making grade.As shown in Figure 1, between grade
The air-flow f of leakage is often returned among sprue with the direction for approaching vertical upstream incoming flow F, the close runner with upstream incoming flow F
The air-flow of wall surface C blends.
As shown in fig. 7, the air-flow of the close runner wall surface C of upstream incoming flow F includes air-flow L1 and mainstream in boundary-layer
Close to the air-flow L2 of boundary-layer in area.The flow velocity S of air-flow L1 in boundary-layer is respectively less than the air-flow in main flow area close to boundary-layer
The 99% of the flow velocity Z of L2, and the flow velocity S of the air-flow L1 in runner wall surface C, boundary-layer is smaller.
When the thickness of boundary-layer is larger, the air-flow that is leaked between grade in the air-flow of the close runner wall surface C of upstream incoming flow F
The ratio of air-flow L1 in the boundary-layer that f is blended is with regard to larger, that is to say, that when the thickness of boundary-layer is larger, between grade
The air-flow of the close runner wall surface C for the upstream incoming flow F that the air-flow f of leakage is blended is mainly the air-flow L1 in boundary-layer, by
It is very low in the flow velocity of the air-flow L1 in boundary-layer, therefore the close stream of upstream incoming flow F that the air-flow f leaked between grade is blended
The flow velocity of the air-flow of road wall surface C is with regard to relatively low.
As shown in figure 5, the thickness of boundary-layer is larger in a comparative example, lead to the stream of the air-flow close to runner wall surface C
Fast V2 is lower, and the flow velocity V1 of the air-flow f leaked between grade is also very low.The air-flow f leaked between the air-flow and grade of runner wall surface C
After blending, biggish blending region M1 is formd, results in biggish starting loss.The flow velocity V of air-flow after blending is
The vector sum of flow velocity V2 and flow velocity V1.
To solve the above problems, needing to increase the flow velocity V2 of the air-flow close to runner wall surface C.As shown in figure 3, suction is facial
Divide 221 there is the first groove structure 221a, pressure face part 222 has the second groove structure 222a；It is circumferentially adjacent for energy
Two rotor blades 2 being set on rotor drum 1, the of the suction surface part 221 of the listrium 22 of one of rotor blade 2
One groove structure 221a is combined with the second groove structure 222a of the pressure face part 222 of the listrium 22 of another rotor blade 2
Splicing, to form runner wall surface C between two rotor blades 2 of circumferentially adjacent setting, flow path wall face has circumferentially
Multiple groove 22a of distribution wave-shaped evenly；
Groove 22a along the runner of two adjacent rotor blades 2 direction extend, and the depth of groove 22a along
Runner direction is gradually increased；The terminal that groove 22a extends is located in the side wall surface of listrium 22.The side wall surface be and runner wall surface C
The plane of intersection.As shown in figure 4, point E, F, G, H are respectively positioned in the side wall surface.
Since the depth of groove 22a is gradually increased along extending direction, groove 22a can preferably accommodate attached
Air-flow L1 in surface layer.Thus, groove 22a can make the gas in boundary-layer during following 1 high-speed rotation of rotor drum
It flows L1 and generates stronger vortex, and then strengthen the momentum-exchange between the air-flow L1 in boundary-layer and the air-flow in main flow area,
So that the thickness of the air-flow L1 in boundary-layer reduces.Comparison diagram 7 is to Fig. 8, after the thickness of the air-flow L1 in boundary-layer reduces,
Thickness in main flow area close to the air-flow L2 of boundary-layer increases.Referring again to Fig. 6, after technical solution of the present invention, close to stream
The flow velocity V2 of the air-flow of road wall surface C is significantly greater than in Fig. 5 close to the flow velocity V2 of the air-flow of runner wall surface C, so that corresponding blending
The area of region M2 is smaller, so that aerodynamic loss caused by leaking between reducing grade, improves compressor efficiency and surge margin.
As shown in figure 3, in one embodiment, the starting point that groove 22a extends is apart from leading edge 20a certain distance L.Groove
Chord length of the starting point that 22a extends apart from leading edge 20a20% to 30%, the depth for the starting point that groove 22a extends is zero.Fig. 3 shows
The starting point D of groove 22a extension is gone out.
In another embodiment, the terminal that the depth of groove 22a extends from the starting point that groove 22a extends to groove 22a
The gradual change in the form of conic section.The depth of groove 22a changes in the rate that front half section changes less than the second half section along extending direction
Rate.
In conjunction with Fig. 3 and Fig. 4, multiple groove 22a are circumferentially uniformly distributed in the form of SIN function or cosine function.?
In circumferential direction, position (position of point E, H in such as Fig. 4) that the blade 20 of multiple groove 22a and two rotor blades 2 is separately connected
It is in crest location.
With continued reference to Fig. 4, in the circumferential, all crest location F and original inner flow passage of multiple groove 22a are in same type
On face, all wave trough position G are in the lowermost end of multiple groove 22a.
For the structural strength for guaranteeing listrium 22, the depth of groove 22a is approximately equal to boundary layer thickness, and is less than or equal to
The half of 22 thickness of listrium.In one embodiment, the quantity of multiple groove 22a is 6 to 12.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this field skill
Art personnel without departing from the spirit and scope of the present invention, can make possible variation and modification, all without departing from this hair
The content of bright technical solution, according to the technical essence of the invention any modification to the above embodiments, equivalent variations and repair
Decorations, each fall within the protection scope that the claims in the present invention are defined.
Claims (12)
1. a kind of rotor blade is suitably mounted on the rotor drum (1) of the rotor of axial flow compressor (100), including blade
(20), tenon (21) and listrium (22)；The blade (20) has suction surface (201) and pressure face (202), and along air-flow side
To with leading edge (20a) and trailing edge (20b)；
It is characterized in that, the listrium (22) includes being located at the suction surface part (221) of the suction surface (201) side and being located at
The pressure face part (222) of pressure face (202) side；The suction surface part (221) has the first groove structure
(221a), the pressure face part (222) have the second groove structure (222a)；
For can circumferentially adjacent two rotor blades (2) being set on the rotor drum (1), described in one of them
First groove structure (221a) of the suction surface part (221) of the listrium (22) of rotor blade (2) with it is another
Second groove structure (222a) of the pressure face part (222) of the listrium (22) of a rotor blade (2)
It is combined and spliced, to form runner wall surface (C) between two rotor blades (2) of circumferentially adjacent setting, the runner
Wall surface has multiple grooves (22a) of circumferentially equably distribution wave-shaped；
The groove (22a) extends along the runner direction of two rotor blades (2), and the depth of the groove (22a) is suitable
Runner direction be gradually increased；The terminal that the groove (22a) extends is located in the side wall surface of the listrium (22).
2. rotor blade as described in claim 1, which is characterized in that the starting point that the groove (22a) extends is before described
The depth of edge (20a) certain distance (L), the starting point that the groove (22a) extends is zero.
3. rotor blade as claimed in claim 2, which is characterized in that the starting point that the groove (22a) extends is before described
The chord length of edge (20a) 20% to 30%.
4. rotor blade as described in claim 1, which is characterized in that the depth of the groove (22a) is from the groove (22a)
Terminal gradual change in the form of conic section that the starting point of extension to the groove (22a) extends.
5. rotor blade as described in claim 1, which is characterized in that the depth of the groove (22a) exists along extending direction
The rate of front half section variation is less than the rate of second half section variation.
6. rotor blade as described in claim 1, which is characterized in that multiple grooves (22a) are circumferentially with SIN function
Or the form of cosine function is uniformly distributed.
7. rotor blade as described in claim 1, which is characterized in that in the circumferential, multiple grooves (22a) and two institutes
It states the position that the blade (20) of rotor blade (2) is separately connected and is in crest location.
8. rotor blade as described in claim 1, which is characterized in that in the circumferential, all waves of multiple grooves (22a)
Peak position and original inner flow passage are on same type face, and all wave trough positions are in the lowermost end of multiple grooves (22a).
9. rotor blade as described in claim 1, which is characterized in that the depth of the groove (22a) is less than or equal to institute
State the half of listrium (22) thickness.
10. rotor blade as described in claim 1, which is characterized in that the quantity of multiple grooves (22a) is 6 to 12.
11. a kind of axial flow compressor, special including casing (100a) and the rotor and stator that are set in the casing (100a)
Sign is that the rotor includes rotor drum (1) and the rotor leaf as described in any one of claims 1 to 10 claim
Piece (2), the rotor blade (2) are mounted on the rotor drum (1), and the rotor drum (1) can be followed to rotate.
12. axial flow compressor as claimed in claim 11, which is characterized in that the stator is fixed on the casing (100a)
On；The stator includes the stator blade (3) along the distribution of airflow direction multistage, and the stator blade (3) is inwardly stretched, and is passed through
Labyrinth gas seals structure (4) surrounds the rotor drum (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810097806.5A CN110094364B (en) | 2018-01-31 | 2018-01-31 | Rotor blade and axial flow compressor |
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| CN201810097806.5A CN110094364B (en) | 2018-01-31 | 2018-01-31 | Rotor blade and axial flow compressor |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN111946666A (en) * | 2020-07-20 | 2020-11-17 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| CN113898421A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Compressor stator inner ring and rotor stator sealing connection structure thereof |
| CN113914999A (en) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | Gas turbine compressor assembling method |
| CN114382555A (en) * | 2020-10-16 | 2022-04-22 | 中国航发商用航空发动机有限责任公司 | Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09317696A (en) * | 1996-05-27 | 1997-12-09 | Toshiba Corp | Stator blade structure of axial flow compressor |
| CN104220758A (en) * | 2012-04-19 | 2014-12-17 | 斯奈克玛 | Compressor casing comprising cavities having an optimised upstream shape |
| WO2015009537A1 (en) * | 2013-07-15 | 2015-01-22 | United Technologies Corporation | Cooled compressor |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN106382260A (en) * | 2016-10-14 | 2017-02-08 | 中国科学院工程热物理研究所 | Gas compressor chordwise groove flow guiding sheet type casing treatment method and device |
| CN206449022U (en) * | 2016-12-02 | 2017-08-29 | 中国航发商用航空发动机有限责任公司 | Processing structure is leaked between multi stage axial flow compressor level |
| CN107110025A (en) * | 2015-04-14 | 2017-08-29 | 三菱日立电力系统株式会社 | The manufacture method of gas turbine |
-
2018
- 2018-01-31 CN CN201810097806.5A patent/CN110094364B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09317696A (en) * | 1996-05-27 | 1997-12-09 | Toshiba Corp | Stator blade structure of axial flow compressor |
| CN104220758A (en) * | 2012-04-19 | 2014-12-17 | 斯奈克玛 | Compressor casing comprising cavities having an optimised upstream shape |
| WO2015009537A1 (en) * | 2013-07-15 | 2015-01-22 | United Technologies Corporation | Cooled compressor |
| CN107110025A (en) * | 2015-04-14 | 2017-08-29 | 三菱日立电力系统株式会社 | The manufacture method of gas turbine |
| CN205001254U (en) * | 2015-09-29 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Rotor blade dish, compressor and aeroengine |
| CN106382260A (en) * | 2016-10-14 | 2017-02-08 | 中国科学院工程热物理研究所 | Gas compressor chordwise groove flow guiding sheet type casing treatment method and device |
| CN206449022U (en) * | 2016-12-02 | 2017-08-29 | 中国航发商用航空发动机有限责任公司 | Processing structure is leaked between multi stage axial flow compressor level |
Non-Patent Citations (2)
| Title |
|---|
| 孙晓治: "转速对压气机级间蓖齿封严影响的实验", 《航空动力学报》 * |
| 沙心国: "高负荷多级轴流压气机级间引气数值模拟", 《航空动力学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN111946666A (en) * | 2020-07-20 | 2020-11-17 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| CN111946666B (en) * | 2020-07-20 | 2022-04-19 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| CN114382555A (en) * | 2020-10-16 | 2022-04-22 | 中国航发商用航空发动机有限责任公司 | Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate |
| CN113898421A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Compressor stator inner ring and rotor stator sealing connection structure thereof |
| CN113914999A (en) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | Gas turbine compressor assembling method |
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| CN110094364B (en) | 2020-05-22 |
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