CN110735806A - stator blade measuring structure - Google Patents
stator blade measuring structure Download PDFInfo
- Publication number
- CN110735806A CN110735806A CN201910936619.6A CN201910936619A CN110735806A CN 110735806 A CN110735806 A CN 110735806A CN 201910936619 A CN201910936619 A CN 201910936619A CN 110735806 A CN110735806 A CN 110735806A
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- CN
- China
- Prior art keywords
- measuring
- stator
- stator blade
- blade
- channel
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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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
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of compressor interstage parameter testing, and particularly relates to an stator blade measuring structure which comprises a stator blade and a plurality of measuring channels, wherein the stator blade is internally provided with the plurality of measuring channels, the end of each measuring channel is the th end, the end of each measuring channel is the second end, the th end of each measuring channel extends to the front edge of the stator blade, the second end of each measuring channel extends to the shroud of the stator blade, and the measuring sensing parts are arranged corresponding to the th ends of measuring channels.
Description
Technical Field
The application belongs to the technical field of compressor interstage parameter testing, and particularly relates to a measuring structure for stator blades.
Background
The compressor is an important part of an aeroengine and a gas turbine, a great amount of tests are required in the development process of the compressor to obtain corresponding interstage parameters, the interstage parameters are mostly obtained based on measurement of modified stator blades, and the currently modified stator blades have the following defects:
1) the measurement sensitive part is mostly welded on the stator blade, the process is unstable, the influence of manpower is great, the installation position is difficult to be ensured, and the measurement precision of the interstage parameter is influenced;
2) the measuring sensitive part, the lead and the patch are positioned on the surface of the stator blade, so that the pneumatic profile of the stator blade is damaged, and the blocking effect of a flow passage of the gas compressor is easily caused.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide stator vane measurement configurations that overcome or mitigate at least the drawbacks of the prior art in terms of .
The technical scheme of the application is as follows:
A stator blade measurement structure, comprising:
the stator blade is internally provided with a plurality of measuring channels, wherein the end of each measuring channel is a -th end, and the end of each measuring channel is a second end;
and a plurality of measuring sensitive parts, wherein each measuring sensitive part is arranged at the th end of measuring channels.
According to at least embodiments of the present application, the stator vanes, each of the sensory portions are body molded.
According to at least embodiments of the present application, the stator vanes, each of the sensitive parts are additively manufactured.
According to at least embodiments of the present application, the stator vane, each of the sensed portions, selects an additive manufacturing process route from a leading edge direction of the stator vane to a trailing edge direction thereof.
According to at least embodiments of the present application, each measurement sensitive portion is in transition connection with the basin and the back of the stator blade.
According to at least embodiments of the present application, each measurement channel is curved with a large rounded transition inside the stator vane.
According to at least embodiments of the present application, the radius of the pilot circle of each measurement channel is located between and two-thirds of the chord length of the stator vane.
According to at least embodiments of the present application, each measurement receptor is connected to a leading edge tapered smooth transition.
According to at least embodiments of the present application, further comprising:
and an upper journal arranged on the blade shroud and provided with a plurality of communication channels therein, wherein the end of each communication channel is correspondingly communicated with the second ends of the measuring channels, and the other end extends to the surface of the upper journal in a way of facing away from the stator blade.
According to at least embodiments of the present application, further comprising:
and the lower journal is arranged on the blade root of the stator blade.
Drawings
FIG. 1 is a schematic view of a stator blade measurement structure provided by an embodiment of the present application;
FIG. 2 is a partial schematic view of a stator blade measurement structure provided by an embodiment of the present application;
wherein:
1-stator blade; 2-a measurement channel; 3-measuring the sensitive part; 4-upper journal; 5-lower journal.
Detailed Description
The present application is described in further detail below at with reference to the drawings and examples, it being understood that the specific examples described herein are for purposes of illustration only and are not intended to limit the application.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are for convenience of description only, and do not indicate or imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus are not to be construed as limiting the present application.
In addition, it should be noted that, unless otherwise expressly stated or limited in this specification, the terms "mounted," "connected," and "connected" shall be construed , and include, for example, fixed or removable connections or physical connections, mechanical or electrical connections, direct or indirect connections through intervening media, and communication between two elements.
The present application is further described in detail at with reference to fig. 1-2.
A stator blade measurement structure, comprising:
the stator blade 1 is internally provided with a plurality of measuring channels 2, wherein the end of each measuring channel 2 is a -th end, and the end of each measuring channel 2 is a second end;
and a plurality of measuring sensors 3, wherein each measuring sensor 3 is arranged at the th end of measuring channels 2.
For the stator blade measuring structure disclosed in the above embodiment, it can be understood by those skilled in the art that the measuring channel 2 can be used for passing a lead wire through the corresponding measuring sensing part 3, so as to be able to measure the compressor interstage parameter.
For the stator blade measuring structure disclosed in the above embodiment, it can be further understood by those skilled in the art that the measuring channels 2 are located inside the stator blade 1 for leading wires, so as to avoid damage of the leading wires to the aerodynamic profile of the stator blade 1, and each of the measuring sensitive parts 3 is correspondingly arranged at the end of measuring channels 2, that is, each of the measuring sensitive parts 3 is located at the front edge of the stator blade 1, so that the aerodynamic profile of the stator blade 1 can be greatly protected, and the blocking effect of the compressor flow channel can be reduced.
In alternative embodiments, the stator vanes 1, each of the sensitive parts 3 are formed integrally.
In alternative embodiments, the stator vanes 1, each of the sensitive parts 3 are additively manufactured.
For the stator blade measurement structure disclosed in the above embodiment, it can be understood by those skilled in the art that the stator blade 1 and each of the sensed portions 3 are formed by an additive manufacturing process , so that the process stability is high, the design position of each of the sensed portions 3 can be effectively ensured, and the measurement accuracy of the compressor interstage parameter is improved.
In alternative embodiments, the stator blade 1 and each sensitive part 3 select an additive manufacturing process route from the leading edge direction of the stator blade 1 to the trailing edge direction thereof, so as to ensure the precise position of each measured sensitive part 3 to the maximum extent and avoid the phenomenon that the time interval for melting and solidifying each layer of metal powder is longer due to the larger forming plane, so that the larger residual stress is caused and the larger deformation is caused.
In alternative embodiments, each measurement sensing part 3 is in transition connection with the basin and the back of the stator blade 1 to reduce the influence of each sensing part 3 on the flow field in the flow channel of the compressor, and the structural design can provide enough strength support for each measurement sensing part 3.
In optional embodiments, each measurement channel 2 is bent in a large circle-guiding transition manner inside the stator blade 1, so as to avoid manufacturing defects caused by small turning angles of each measurement channel 2 in the additive manufacturing process, and ensure the internal structural characteristics of each measurement channel 2, and in addition, designing each measurement channel 2 in a large circle-guiding transition manner inside the stator blade 1 can effectively improve the manufacturability, and meanwhile, the measurement channel is coordinated with the blade profile curved surface of the stator blade 1, and enough margins are left on two sides of the blade basin and the blade back of the stator blade 1 to ensure the residual strength of the stator blade 1.
In alternative embodiments, the radius of the circle of each measuring channel 2 is between and two thirds of the chord length of the stator vane 1.
In alternative embodiments, each of the sensing units 3 is connected with a leading edge tapered smooth transition to reduce the influence of each of the sensing units 3 on the flow field in the compressor flow passage.
In some optional embodiments, further comprising:
and an upper shaft journal 4 arranged on the blade shroud and provided with a plurality of communication channels, wherein the end of each communication channel is correspondingly communicated with the second ends of the measuring channels 2, and the other end extends to the surface of the upper shaft journal 4 opposite to the stator blade 1.
For the stator blade measuring structure disclosed in the above embodiment, it can be understood by those skilled in the art that each communicating channel in the upper journal 4 on the shroud of the stator blade 1 is communicated with each corresponding measuring channel 2 to form a lead channel, and this design does not affect the assembly and structural functions of the stator blade 1, and also facilitates the lead test modification.
In some optional embodiments, further comprising:
and a lower journal 5 disposed on a blade root of the stator blade 1.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1, kind of stator blade measurement structure, its characterized in that includes:
the stator blade (1) is internally provided with a plurality of measuring channels (2), the end of each measuring channel (2) is an th end, and the other end of each measuring channel is a second end, the th end of each measuring channel (2) extends to the front edge of the stator blade (1), and the second end of each measuring channel extends to the tip shroud of the stator blade (1);
a plurality of measuring sensitive parts (3), wherein each measuring sensitive part (3) is arranged at the th end of measuring channels (2).
2. The stator vane measuring structure of claim 1,
the stator blade (1) and each of the sensitive parts (3) are molded integrally.
3. The stator vane measuring structure according to claim 2,
the stator blade (1) and each of the sensitive parts (3) are manufactured in an additive mode.
4. The stator vane measuring structure according to claim 3,
the stator blade (1) and each of the sensitive parts (3) select an additive manufacturing process route from the front edge direction of the stator blade (1) to the tail edge direction thereof.
5. The stator vane measuring structure according to claim 3,
each measuring sensitive part (3) is in conductive circle transitional connection with a blade basin and a blade back of the stator blade (1).
6. The stator vane measuring structure of claim 5,
each measuring channel (2) is bent in a large circle transition inside the stator blade (1).
7. The stator vane measuring structure of claim 6,
the radius of the circle of each measuring channel (2) is between and two thirds of the chord length of the stator blade (1).
8. The stator vane measuring structure of claim 1,
each measuring sensitive part (3) is connected with the front edge in a tapered smooth transition mode.
9. The stator vane measuring structure of claim 1,
further comprising:
an upper journal (4) is arranged on the blade shroud and is provided with a plurality of communication channels, ends of each communication channel are correspondingly communicated with the second ends of measuring channels (2), and the other ends extend to the surface of the upper journal (4) opposite to the stator blade (1).
10. The stator vane measuring structure of claim 1,
further comprising:
a lower journal (5) arranged on the blade root of the stator blade (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910936619.6A CN110735806A (en) | 2019-09-29 | 2019-09-29 | stator blade measuring structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910936619.6A CN110735806A (en) | 2019-09-29 | 2019-09-29 | stator blade measuring structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110735806A true CN110735806A (en) | 2020-01-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910936619.6A Pending CN110735806A (en) | 2019-09-29 | 2019-09-29 | stator blade measuring structure |
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|---|---|
| CN (1) | CN110735806A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111561478A (en) * | 2020-05-22 | 2020-08-21 | 中国航发沈阳发动机研究所 | Stator blade measurement integrated structure |
| CN114215780A (en) * | 2021-12-06 | 2022-03-22 | 中国航发沈阳发动机研究所 | Compressor interstage total temperature measurement structure |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| CN204572555U (en) * | 2015-04-21 | 2015-08-19 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of stator blade of reserved inter-stage test hole |
| CN204628095U (en) * | 2015-02-12 | 2015-09-09 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of compressor stator blade |
| CN105485056A (en) * | 2015-12-25 | 2016-04-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Stator blade mounting structure of air compressor |
| CN107701514A (en) * | 2017-09-30 | 2018-02-16 | 中国航发沈阳发动机研究所 | Stator blade structure is measured between compressor stage |
| CN109098997A (en) * | 2018-07-19 | 2018-12-28 | 中国航发沈阳发动机研究所 | A kind of compressor passage aerodynamic parameter measurement method |
| CN109937103A (en) * | 2016-11-10 | 2019-06-25 | 赛峰直升机发动机公司 | Method for manufacturing turbine blade |
| CN110005474A (en) * | 2019-04-18 | 2019-07-12 | 中国航发沈阳发动机研究所 | A kind of stator component and the aero-engine with it |
-
2019
- 2019-09-29 CN CN201910936619.6A patent/CN110735806A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037473A (en) * | 1971-09-16 | 1977-07-26 | International Harvester Company | Radiation pyrometers with purging fluid |
| CN204628095U (en) * | 2015-02-12 | 2015-09-09 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of compressor stator blade |
| CN204572555U (en) * | 2015-04-21 | 2015-08-19 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of stator blade of reserved inter-stage test hole |
| CN105485056A (en) * | 2015-12-25 | 2016-04-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Stator blade mounting structure of air compressor |
| CN109937103A (en) * | 2016-11-10 | 2019-06-25 | 赛峰直升机发动机公司 | Method for manufacturing turbine blade |
| CN107701514A (en) * | 2017-09-30 | 2018-02-16 | 中国航发沈阳发动机研究所 | Stator blade structure is measured between compressor stage |
| CN109098997A (en) * | 2018-07-19 | 2018-12-28 | 中国航发沈阳发动机研究所 | A kind of compressor passage aerodynamic parameter measurement method |
| CN110005474A (en) * | 2019-04-18 | 2019-07-12 | 中国航发沈阳发动机研究所 | A kind of stator component and the aero-engine with it |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111561478A (en) * | 2020-05-22 | 2020-08-21 | 中国航发沈阳发动机研究所 | Stator blade measurement integrated structure |
| CN114215780A (en) * | 2021-12-06 | 2022-03-22 | 中国航发沈阳发动机研究所 | Compressor interstage total temperature measurement structure |
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Application publication date: 20200131 |