CN111271322B - Adjustable stationary blade and compressor - Google Patents
Adjustable stationary blade and compressor Download PDFInfo
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- CN111271322B CN111271322B CN201811478879.5A CN201811478879A CN111271322B CN 111271322 B CN111271322 B CN 111271322B CN 201811478879 A CN201811478879 A CN 201811478879A CN 111271322 B CN111271322 B CN 111271322B
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- blade
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- inlet end
- gas channel
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0238—Details or means for fluid reinjection
-
- 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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
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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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
Abstract
The invention relates to an adjustable stationary blade, a blade tip flow field adjusting method thereof and a gas compressor. Wherein the adjustable vane comprises a blade; an adjusting part for adjusting the rotation angle of the blade; and the inlet end of the first gas channel is arranged on the adjusting part, the outlet end of the first gas channel is positioned in the top area of the suction surface of the blade, the first gas channel extends from the inlet end in the adjusting part, enters the inside of the blade from the blade tip of the blade, and then extends to the outlet end of the blade from the inside of the blade. The adjustable stationary blade, the adjusting method and the compressor have the advantages of small flow loss, stable and reliable operation and the like.
Description
Technical Field
The invention relates to an adjustable stationary blade, an air compressor and a blade tip flow field adjusting method.
Background
The fixed blades of the first stages of the aero-engine compressor generally adopt adjustable fixed blades with adjustable installation angles. When the compressor works at a non-designed rotating speed, the angles of the adjustable stationary blades of the previous stages need to be adjusted to adapt to the working state of the compressor. In addition, when the performance test is carried out on the air compressor in the design stage, the angle of the adjustable stationary blade can be adjusted at the design rotating speed, and the angle optimization test of the adjustable stationary blade is carried out. Because the casing of the compressor is arc-shaped in the circumferential direction, after the angle of the adjustable stationary blade is adjusted, a gap is generated between the blade tip and the casing. The larger the adjustable vane angle is adjusted, the larger the blade tip clearance is.
The adjustable stationary blade tip generates a gap which is unfavorable for the flow field of the compressor. Static pressure on the pressure surface side of the adjustable static blade is larger than static pressure on the suction surface side, a gap is generated on the blade tip, airflow flows from the pressure surface side to the suction surface side, and blade tip leakage flow is generated. Tip leakage flow can increase flow loss and reduce compressor performance. The larger the angle adjustment of the adjustable stationary blade is, the larger the blade tip clearance is, and the larger the influence on the pneumatic performance of the compressor is.
In the research of blade tip clearance flow, the research on a rotor is more, and because a stator is generally directly and fixedly arranged on a casing and is in seamless connection with the casing, the blade tip clearance influence of the stator of the compressor is rarely concerned. Due to the special angle-adjustable structure of the adjustable stationary blade, a gap can be generated between the blade tip of the stator and the casing. The inventor finds that the blade tip clearance of the adjustable stationary blade has certain influence on the pneumatic performance of the compressor, particularly when the adjusting angle of the stationary blade at the medium and low rotating speeds is large, the blade tip leakage flow is obvious, and the influence on the pneumatic performance of the compressor cannot be ignored. Therefore, there is a need in the art for an adjustable vane structure and a method for adjusting a tip flow field that optimizes the flow field in the adjustable vane tip clearance region to improve the aerodynamic performance of the compressor.
Disclosure of Invention
It is an object of the present invention to provide an adjustable vane.
Another object of the present invention is to provide a compressor.
It is a further object of the present invention to provide a method of adjusting a tip flow field of an adjustable vane.
An adjustable stator vane according to an aspect of the present invention includes a blade; an adjusting part for adjusting the rotation angle of the blade; and the inlet end of the first gas channel is arranged in the adjusting part, the outlet end of the first gas channel is positioned on the suction surface of the top area of the blade, and the first gas channel extends from the inlet end of the first gas channel in the adjusting part, enters the interior of the blade from the blade tip of the blade and then extends from the interior of the blade to the outlet end of the blade.
In an embodiment of the adjustable vane, the outlet end comprises at least one air outlet on each side of the chordal midline of the adjustable vane.
In an embodiment of the adjustable vane, the number of the air outlets is 4-20.
A compressor according to another aspect of the present invention comprises the adjustable vane described in any one of the above; and a casing for fixing the adjusting portion of the adjustable stationary blade, the casing including a second gas passage having an inlet end located on a high pressure side of the adjustable stationary blade and an outlet end connected to an inlet end of the first gas passage to output gas to the first gas passage.
In an embodiment of the compressor, the compressor further comprises a rotor blade adjacent downstream to the adjustable vane, and the inlet end of the second gas channel is located at an upper portion of the casing corresponding to a tip of the rotor blade.
In an embodiment of the compressor, the inlet end of the second gas passage is located at a position of the casing corresponding to a chordwise middle-rear section of the rotor blade.
In an embodiment of the compressor, the inlet end of the first gas passage includes a first boundary and a second boundary defining an opening size thereof, the first boundary and the second boundary being always located outside of an outlet end of the second gas passage when the vane rotates between the first critical position and the second critical position.
In an embodiment of the compressor, the cross-sectional shape of the inlet end of the first gas passage is a sector.
In an embodiment of the compressor, each of the adjustable stationary blades corresponds to an inlet end of a second gas passage at the same circumferential position.
A method of adjusting a tip flow field of an adjustable vane according to yet another aspect of the present invention includes:
and extracting the gas, conveying the gas to the top area of the suction surface of the adjustable stationary blade through the inside of the adjustable stationary blade, and blowing the gas out.
In summary, the improvement effect of the present invention at least includes one of the following:
1. the outlet end is arranged on the suction surface of the top area of the adjustable stationary blade, and airflow is blown out from the outlet end, so that the pressure difference on two sides of the blade tip clearance is reduced, the blade tip leakage flow is weakened, the flow field is improved, and the blade tip leakage flow loss is reduced;
2. because the outlet end is arranged on the blade of the adjustable stationary blade, when the adjustable stationary blade rotates, the position of the outlet end rotates along with the blade, and the position of the blade tip leakage flow can be accurately positioned;
3. when the angle of the adjustable stationary blade is in the initial position, no clearance exists at the blade tip, the outlet end of the blade surface can improve the flow of the stationary blade angle area, and the flow loss is reduced;
4. in the gas compressor, the upper parts of the blade tips of the adjacent rotor blades of the adjustable stationary blade are subjected to air extraction to extract low-energy fluid masses leaked from the tip part of the rotor, so that the flow field of the tip part of the downstream rotor is improved, the working capacity of the rotor is improved, and the stability margin of the gas compressor is improved;
5. in the air compressor, a special structure is adopted for an air-entraining channel from a casing to an adjustable stationary blade adjusting part, so that the channel can continuously ventilate when blades rotate.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments in conjunction with the accompanying drawings, it being noted that the drawings are given by way of example only and are not drawn to scale, and should not be taken as limiting the scope of the invention which is actually claimed, wherein:
FIG. 1 is a schematic view of a gas channel structure according to an embodiment of the present invention.
Fig. 2 is a sectional view taken along line a-a of fig. 1.
FIG. 3 is a schematic view of the outlet end of the first gas channel of one embodiment of the present invention.
FIGS. 4A and 4B are tip leakage flow comparison schematics of an adjustable vane employing an embodiment of the present invention.
The reference numbers in the drawings are as follows:
1: a rotor blade;
2: rotor tip clearances;
3: an inlet end of the second gas channel;
4: a compressor casing;
5: a second gas passage;
6: a second gas passage outlet end;
7: an inlet end of the first gas channel;
8: an adjustment section;
9: the blade tip clearance of the static blade can be adjusted;
10: a first gas passage outlet end;
11: a first gas passage;
12: an adjustable stationary blade.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
Further, it is to be understood that the positional or orientational relationships indicated by the terms "front, rear, upper, lower, left, right", "transverse, vertical, horizontal" and "top, bottom" and the like are generally based on the positional or orientational relationships illustrated in the drawings and are provided for convenience in describing the invention and for simplicity in description, and that these terms are not intended to indicate and imply that the referenced devices or elements must be in a particular orientation or be constructed and operated in a particular orientation without departing from the scope of the invention. Also, this application uses specific language to describe embodiments of the application. The terms "inside" and "outside" refer to the inner and outer parts relative to the outline of each part itself, and the terms "first", "second", "third", and the like are used to define the parts, and are used only for the convenience of distinguishing the corresponding parts, and unless otherwise stated, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Referring to fig. 1, the adjustable vane includes an adjustable vane blade 12 and an adjusting portion 8 for adjusting a rotation angle of the adjustable vane blade 12, and a specific structure of the adjusting portion may be an adjusting handle as shown in fig. 1 and 2, but is not limited thereto. With continuing reference to fig. 1, the adjustable stationary blade further includes a first gas channel 11 for adjusting the flow field of the tip clearance 9, the inlet end 7 of the first gas channel is disposed on the adjusting portion 8, with reference to fig. 1 and 3, the outlet end 10 of the first gas channel is located on the suction surface of the top region of the adjustable stationary blade 12, the top region is defined as the region within 10% of the blade height below the blade tip of the adjustable stationary blade 12, the suction surface of the region is provided with the outlet end of the gas channel 11 to improve the flow field principle, as shown in fig. 1, 4A and 4B, when the gas outlet end is not provided, as shown in fig. 4A, the static pressure difference between the two sides of the tip clearance 9 is larger, and after the gas outlet end is provided by using the suction surface of the top region, as shown in fig. 4B, the static pressure on the suction surface side of the adjustable stationary blade can be increased, thereby reducing the static pressure difference between the two sides of the, therefore, the leakage flow of the blade tip is weakened, the flow field of the blade tip is improved, and the flow loss is reduced. A first flow channel 11 for gas flow in the adjustable vane has a structure, referring to fig. 1, wherein the first gas channel 11 extends from the inlet end 7 thereof in the adjusting part 8 and from the tip of the adjustable vane blade 12 into the interior of the blade 12 and from the interior of the blade 12 to the outlet end 10 thereof. Meanwhile, the air outlet end 10 is arranged on the blade of the adjustable stationary blade, and when the adjustable stationary blade 12 rotates, the air outlet end 10 rotates along with the blade, so that the blade tip leakage flow position can be accurately positioned. Moreover, when the rotation angle position of the adjustable stationary blade 12 is at the initial position, the blade tip has no clearance, and the gas outlet end 10 opened on the surface of the adjustable stationary blade 12 can improve the flow in the stationary blade angle region and also play a role in reducing the flow loss.
With continued reference to fig. 1 and 3, an example of a specific distribution of the outlet end 10 at the adjustable vane blade 12 may be that the outlet end 10 includes at least one outlet port on each of two sides of the chordwise midline of the adjustable vane blade 12, which may further improve the tip flow field. In one embodiment shown in fig. 1 and 3, the outlet end 10 is configured such that two outlets are provided on each of two sides of the chordwise centerline of the adjustable stationary blade 12. The number of the air outlets is optimized and adjusted according to the specific chord length of the blades and the specific working condition requirement of the compressor, and the preferred number is 4-20.
With continued reference to fig. 1, the specific structure of the compressor matching the adjusting portion 8 of the adjustable stationary blade and the first gas channel 11 may be, in an embodiment, a casing 4 of the compressor is used for fixing the adjusting portion 8, and a second gas channel 5 is provided in the casing 4, an inlet end 3 of the second gas channel 5 is located on a high pressure side of the adjustable stationary blade, i.e. a side with a higher pressure than the adjustable stationary blade, and an outlet end 6 of the second gas channel 5 is connected to an inlet end 7 of the first gas channel 11, and the gas flows through a path that the gas enters the inlet end 3 of the second gas channel 5 from the high pressure side, passes through the second gas channel 5, and enters the inlet end 7 of the first gas channel 11 from the outlet end 6 of the second gas channel 5. Preferably, each adjustable stationary blade corresponds to the inlet end 3 of the second gas channel 5, the number of the inlet ends 3 of the second gas channels 5 is the same as that of the adjustable stationary blades, and meanwhile, the circumferential position of the inlet end 3 of the second gas channel 5 is also the same as that of the adjustable stationary blades, so that the one-to-one correspondence ensures the amount of gas entering the adjustable stationary blades and simplifies the design of the gas flow channel structure.
With continued reference to fig. 1, the specific location of the high pressure side may be, in one embodiment, that the inlet end 3 of the second gas channel 5 is located downstream of the adjustable vane and in the upper part of the tip of the rotor blade 1 adjacent to the adjustable vane. The tip of the rotor blade 1 of the downstream rotor blade 1 is pumped by pumping air from the upper part of the tip, so that the low-energy fluid mass leaked and flowing from the tip of the rotor blade tip gap 2 of the rotor blade 1 is pumped, the flow field of the tip of the downstream rotor is improved, the working capacity of the rotor is improved, and the stability margin of the gas compressor is improved. Further, with continued reference to FIG. 1, the specific location of the inlet end 3 of the second gas channel 5 may be at a location of the casing 4 corresponding to the chordwise mid-aft section of the rotor blade 1, such that more air may be extracted from the rotor tip location, more tip leakage flow of the rotor blade 1 may be extracted, and more blown air may be provided to the outlet end 10 of the adjustable vane blade 12.
Referring to fig. 1 and 2, the inlet end 7 of the first gas channel 11 includes a first boundary 71 and a second boundary 72 defining the opening size thereof, and when the vane blade 12 rotates between a first critical position and a second critical position of a rotation angle range, the first boundary 71 and the second boundary 72 are always located outside the range of the outlet end 6 of the second gas channel 5, so that the second gas channel 5 and the first gas channel 11 can be continuously communicated when the vane blade 12 rotates, and the gas supply to the outlet end 10 of the first gas channel 11 is ensured. In particular, the inlet end 7 of the first gas channel 11 may be a fan-shaped structure defined by a first boundary 71 and a second boundary 72, which is simple in structure and easy to machine.
In summary, it can be seen from the above description that the method for adjusting the tip flow field of the adjustable stationary blade 12 includes extracting gas, and the gas is delivered to the top region of the suction surface of the adjustable stationary blade 12 through the inside of the adjustable stationary blade 12 and blown out to increase the pressure on the suction surface side of the adjustable stationary blade, so as to reduce the static pressure difference between the two sides of the tip clearance 9 of the adjustable stationary blade, thereby weakening the tip leakage flow, improving the tip flow field, and reducing the flow loss.
In summary, the beneficial effects of the adjustable stationary blade and the compressor adopting the above embodiment may include one of the following:
1. the outlet end is arranged on the suction surface of the top area of the adjustable stationary blade, and airflow is blown out from the outlet end, so that the pressure difference on two sides of the blade tip clearance is reduced, the blade tip leakage flow is weakened, the flow field is improved, and the blade tip leakage flow loss is reduced;
2. because the outlet end is arranged on the blade of the adjustable stationary blade, when the adjustable stationary blade rotates, the position of the outlet end rotates along with the blade, and the position of the blade tip leakage flow can be accurately positioned;
3. when the angle of the adjustable stationary blade is in the initial position, no clearance exists at the blade tip, the outlet end of the blade surface can improve the flow of the stationary blade angle area, and the flow loss is reduced;
4. in the gas compressor, the upper parts of the blade tips of the adjacent rotor blades of the adjustable stationary blade are subjected to air extraction to extract low-energy fluid masses leaked from the tip part of the rotor, so that the flow field of the tip part of the downstream rotor is improved, the working capacity of the rotor is improved, and the stability margin of the gas compressor is improved;
5. in the air compressor, a special structure is adopted for an air-entraining channel from a casing to an adjustable stationary blade adjusting part, so that the channel can continuously ventilate when blades rotate.
Although the present invention has been disclosed in the above-mentioned embodiments, it is not intended to limit the present invention, and those skilled in the art may make variations and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (9)
1. An adjustable vane, comprising:
a blade;
an adjusting part for adjusting the rotation angle of the blade; and
the inlet end of the first gas channel is arranged at the adjusting part, the outlet end of the first gas channel is positioned on the suction surface of the top area of the blade, the first gas channel extends from the inlet end of the first gas channel in the adjusting part, enters the interior of the blade from the blade tip of the blade and then extends to the outlet end from the interior of the blade, and the blade tip of the blade is close to one side of the adjusting part.
2. The adjustable vane of claim 1 wherein the outlet end includes at least one outlet port on each of two sides of the chordal centerline of the adjustable vane.
3. The adjustable vane of claim 2 wherein the number of air outlets is 4-20.
4. An air compressor, characterized by comprising
The adjustable vane of any one of claims 1-3; and
a casing for holding the adjusting portion of the adjustable vane, the casing comprising a second gas channel having an inlet end located on the high pressure side of the adjustable vane and an outlet end connected to the inlet end of the first gas channel for outputting gas to the first gas channel.
5. The compressor of claim 4, further comprising rotor blades adjacent downstream to the adjustable vanes, wherein the inlet end of the second gas passage is located at an upper portion of the casing corresponding to tips of the rotor blades.
6. The compressor of claim 5, wherein an inlet end of the second gas passage is located at a position of the casing corresponding to a chordwise intermediate aft section of the rotor blade.
7. The compressor of claim 4, wherein the inlet end of the first gas passage includes a first boundary and a second boundary defining an opening size thereof, the first boundary and the second boundary being always located outside of the range of the outlet end of the second gas passage when the adjustable vane is rotated between the first critical position and the second critical position.
8. An air compressor as claimed in claim 7, characterised in that the inlet end of the first gas passage is sector-shaped in cross-section.
9. The compressor of claim 4 wherein each of said adjustable vanes respectively corresponds to an inlet end of a second gas passage at the same circumferential position as the respective adjustable vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811478879.5A CN111271322B (en) | 2018-12-05 | 2018-12-05 | Adjustable stationary blade and compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811478879.5A CN111271322B (en) | 2018-12-05 | 2018-12-05 | Adjustable stationary blade and compressor |
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| CN111271322A CN111271322A (en) | 2020-06-12 |
| CN111271322B true CN111271322B (en) | 2020-12-29 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112324713B (en) * | 2020-11-26 | 2022-03-22 | 沈阳航空航天大学 | Airflow corner self-adaptive guide blade of axial-flow compressor and design method thereof |
| CN114876838B (en) * | 2021-02-05 | 2023-08-18 | 中国航发商用航空发动机有限责任公司 | Blade tip gap adjusting structure for impeller adjustable stationary blade and impeller and compressor using same |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09126195A (en) * | 1995-11-01 | 1997-05-13 | Mitsubishi Heavy Ind Ltd | Axial blower |
| FR2933149B1 (en) * | 2008-06-25 | 2010-08-20 | Snecma | AIR INJECTION IN THE VEIN OF A TURBOMACHINE COMPRESSOR |
| US8668444B2 (en) * | 2010-09-28 | 2014-03-11 | General Electric Company | Attachment stud for a variable vane assembly of a turbine compressor |
| FR2970302B1 (en) * | 2011-01-11 | 2015-07-17 | Snecma | DOUBLE FLOW TURBOREACTOR |
| US10280757B2 (en) * | 2013-10-31 | 2019-05-07 | United Technologies Corporation | Gas turbine engine airfoil with auxiliary flow channel |
| JP6421091B2 (en) * | 2015-07-30 | 2018-11-07 | 三菱日立パワーシステムズ株式会社 | Axial flow compressor, gas turbine including the same, and stationary blade of axial flow compressor |
| CN105179322B (en) * | 2015-09-14 | 2017-08-25 | 北京航空航天大学 | Blade root opens up the Profile For Compressor Stator leaf grating of wide straight-line groove |
| DE102016208706A1 (en) * | 2016-05-20 | 2017-11-23 | MTU Aero Engines AG | Guide vane for a Eintrittsleitgitter |
| CN206601239U (en) * | 2016-11-29 | 2017-10-31 | 中国航发商用航空发动机有限责任公司 | Aero-engine multistage compressor test structure and its adjustable flow-guiding stator blade |
| CN107120315A (en) * | 2017-05-16 | 2017-09-01 | 珠海格力电器股份有限公司 | Stator blade, compressor arrangement and compressor |
| CN107228095B (en) * | 2017-07-24 | 2019-01-29 | 北京航空航天大学 | A kind of adaptive compressor improving rotator tip and stator corner region flow |
| CN107165864B (en) * | 2017-07-24 | 2021-02-09 | 北京航空航天大学 | Multistage axial flow compressor with combined self-adaptive adjustment of rotating vanes and fixed vanes |
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