CN111561478A - Stator blade measurement integrated structure - Google Patents
Stator blade measurement integrated structure Download PDFInfo
- Publication number
- CN111561478A CN111561478A CN202010439683.6A CN202010439683A CN111561478A CN 111561478 A CN111561478 A CN 111561478A CN 202010439683 A CN202010439683 A CN 202010439683A CN 111561478 A CN111561478 A CN 111561478A
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- CN
- China
- Prior art keywords
- stator blade
- lead
- channel
- blade
- stator
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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
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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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
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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
- F04D27/001—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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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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
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
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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
- F05D2240/12—Fluid guiding means, e.g. vanes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (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 a stator blade measurement integrated structure, which comprises: the stator blade is internally provided with a bundling channel, and the front edge of the stator blade is provided with a plurality of sensing bulges which are arranged along the axial direction; one end of the bundling channel extends to a blade crown of the stator blade; each induced protrusion is recessed towards the direction of the bundling channel and back to the stator blade to form a lead hole; one end of each test lead penetrates through the bundling channel and correspondingly extends into one lead hole; the plurality of sensing parts are positioned on the surfaces of the sensing bulges far away from the stator blades; each sensing part is correspondingly arranged in one lead hole and is connected with the corresponding test lead.
Description
Technical Field
The application belongs to the technical field of compressor interstage parameter testing, and particularly relates to a stator blade measurement integrated structure.
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 sensitive part is directly welded on the stator blade, so that large residual stress exists, the service life of the stator blade is greatly damaged, the part structure in a flow passage of the compressor is easily damaged by falling off, the compressor is damaged, and the smooth performance of a compressor test is influenced;
2) most of the sensitive parts are welded at the side of a blade basin of the stator blade, so that various parameters cannot be accurately measured, and the test lead wires connected with the sensitive parts are fixed outside the stator blade through titanium sheets in a compression joint mode, so that the appearance of the stator blade is damaged, and the performance of the gas compressor is seriously affected.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
It is an object of the present application to provide a stator blade measurement integrated structure to overcome or mitigate the technical drawbacks of at least one aspect of the known existence.
The technical scheme of the application is as follows:
a stator blade measurement integrated structure, comprising:
the stator blade is internally provided with a bundling channel, and the front edge of the stator blade is provided with a plurality of sensing bulges which are arranged along the axial direction; one end of the bundling channel extends to a blade crown of the stator blade; each induced protrusion is recessed towards the direction of the bundling channel and back to the stator blade to form a lead hole;
one end of each test lead penetrates through the bundling channel and correspondingly extends into one lead hole;
the plurality of sensing parts are positioned on the surfaces of the sensing bulges far away from the stator blades; each sensing part is correspondingly arranged in one lead hole and is connected with the corresponding test lead.
According to at least one embodiment of the present application, in the above stator vane measurement integration structure, the stator vane is integrally formed with each of the sensing protrusions thereon.
According to at least one embodiment of the application, in the stator blade measurement integrated structure, the stator blade and each induced protrusion on the stator blade are manufactured in an additive mode.
According to at least one embodiment of the application, in the stator blade measurement integrated structure, the circumferential small circular angle transition of the connection part of each induced protrusion and the stator blade is realized.
According to at least one embodiment of the present application, in the above stator vane measurement integration structure, each of the sensed portions is glued in the corresponding lead hole.
According to at least one embodiment of the present application, in the stator blade measurement integrated structure, each of the sensing portions is screwed into the corresponding lead hole.
According to at least one embodiment of the present application, in the above stator blade measurement integration structure, the stator blade shroud has an upper journal thereon; the upper shaft neck is provided with a lead channel; one end of the lead channel is communicated with the bundling channel, and the other end of the lead channel extends to the end face of the upper shaft neck, which is back to the stator blade.
According to at least one embodiment of the present application, the stator blade measurement integration structure includes a stator blade root having a lower journal thereon.
The application has at least the following beneficial technical effects:
in the stator blade measurement integrated structure, each sensed part is positioned on the surface of a sensed protrusion far away from the stator blade and on the front edge of the stator blade, and can accurately measure the relevant parameters of a temperature field and a pressure field between compression stages; in addition, each test lead wire passes the inside bundling channel of stator blade, the pin hole is connected to the portion of being sensed that corresponds, by the cladding inside the stator blade, can not destroy the appearance of stator blade, can not cause serious influence to the performance of compressor, and each pin hole and bundling channel intercommunication, each pin hole assembles at bundling channel promptly, communicate to the tip shroud position of stator blade through bundling channel, and be convenient for process, and can avoid the transition to weaken stator blade intensity, each test lead wire gathers in bundling channel and is convenient for manage.
Drawings
FIG. 1 is a schematic structural view of a current modified stator blade;
FIG. 2 is a schematic view of a portion of FIG. 1 in the area A;
FIG. 3 is a schematic structural diagram of a stator blade measurement integrated structure provided by an embodiment of the present application;
FIG. 4 is a partial schematic view of the area B of FIG. 3;
FIG. 5 is a partial schematic view of region C of FIG. 3;
wherein:
1-stator blade; 2-a sensitive bulge; 3-testing the lead; 4-a sensitive part; 5-upper journal; 6-lower journal.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 5.
A stator blade measurement integrated structure, comprising:
the stator blade 1 is provided with a bundling channel inside, and the front edge of the stator blade is provided with a plurality of sensing bulges 2 which are arranged along the axial direction; one end of the bundling channel extends to the blade crown of the stator blade 1; each induced protrusion 2 is recessed towards the direction of the bundling channel, which is opposite to the stator blade 1, to form a lead hole;
one end of each test lead 3 penetrates through the bundling channel and correspondingly extends into one lead hole;
a plurality of sensing parts 4 which are positioned on the surface of the sensing protrusion 2 far away from the stator blade 1; each of the sensing portions 4 is disposed in a corresponding one of the lead holes and connected to a corresponding one of the test leads 3.
For the stator blade measurement integrated structure disclosed in the above embodiment, it can be understood by those skilled in the art that each of the sensed portions 4 is located on the surface of the sensed protrusion 2 away from the stator blade 1, and is located on the leading edge of the stator blade 1, so that the related parameters of the temperature field and the pressure field between the compressor stages can be measured more accurately.
To the stator blade measurement integrated configuration disclosed in the above-mentioned embodiment, a skilled person in the art can also understand that each test lead 3 passes through the bundling channel inside the stator blade 1, the lead hole is connected to the corresponding sensed part 4, and the cladding is inside the stator blade 1, so that the appearance of the stator blade is not damaged, and the performance of the compressor is not seriously affected, and each lead hole is communicated with the bundling channel, that is, each lead hole converges in the bundling channel, and communicates to the tip shroud part of the stator blade 1 through the bundling channel, so that the processing is convenient, and the transient weakening of the strength of the stator blade 1 can be avoided, and each test lead 3 gathers in the bundling channel and is convenient to manage.
In some alternative embodiments, the stator blade measuring integrated structure is formed by integrally forming the stator blade 1 with each of the sensing protrusions 2.
To the stator blade measurement integrated structure disclosed in the above embodiment, those skilled in the art can understand that each of the induced protrusions 2 is integrally formed on the stator blade 1, and is not easy to fall off from the stator blade 1, and does not damage the structure of the part in the flow channel of the compressor, thereby effectively ensuring the smooth performance of the experiment.
In some alternative embodiments, in the stator vane measurement integrated structure, the stator vane 1 and each of the induced protrusions 2 thereon are manufactured by additive manufacturing.
In some optional embodiments, in the stator blade measurement integrated structure, the circumferential small circular angle of the connection part of each induced protrusion 2 and the stator blade 1 is transited so as to effectively reduce the influence on the performance of the compressor.
In some alternative embodiments, in the stator blade measurement integrated structure, each of the sensitive portions 4 is glued or screwed into the corresponding lead hole.
For the stator blade measurement integrated structure disclosed in the above embodiment, it can be understood by those skilled in the art that each sensed part 4 is glued or screwed into the corresponding lead hole, so that the damaged sensed part 4 can be replaced conveniently.
In some alternative embodiments, in the above stator blade measurement integrated structure, the stator blade 1 has an upper journal 5 on the shroud; the upper shaft neck 5 is provided with a lead channel; one end of the lead channel is communicated with the bundling channel, and the other end of the lead channel extends to the end face, back to the stator blade 1, of the upper shaft neck 5.
For the stator blade measurement integrated structure disclosed in the above embodiment, it can be understood by those skilled in the art that one end of each test lead 3 may enter the bundling channel through the lead channel, and then pass through the bundling channel to enter the corresponding lead hole to connect with the corresponding sensing portion 4.
In some alternative embodiments, the stator blade measurement integration structure described above has a lower journal 6 on the blade root of the stator blade 1.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and such changes or substitutions will fall within the scope of the present application.
Claims (8)
1. A stator blade measurement integrated structure, comprising:
the stator blade (1) is internally provided with a bundling channel, and the front edge of the stator blade is provided with a plurality of axially-arranged sensitive bulges (2); one end of the bundling channel extends to a blade crown of the stator blade (1); each induced protrusion (2) is recessed towards the direction of the bundling channel, which is opposite to the stator blade (1), to form a lead hole;
one end of each test lead (3) penetrates through the bundling channel and correspondingly extends into one lead hole;
a plurality of sensitive parts (4) positioned on the surface of the sensitive bulge (2) far away from the stator blade (1); each sensing part (4) is correspondingly arranged in one lead hole and is connected with the corresponding test lead (3).
2. The stator blade measurement integration structure of claim 1,
the stator blade (1) and each sensitive bulge (2) are integrally formed.
3. The stator blade measurement integration structure of claim 2,
the stator blade (1) and each of the induced protrusions (2) thereon are manufactured by additive manufacturing.
4. The stator blade measurement integration structure of claim 1,
the circumferential small circular angle transition of the connecting part of each induced protrusion (2) and the stator blade (1).
5. The stator blade measurement integration structure of claim 1,
each sensitive part (4) is glued in the corresponding lead hole.
6. The stator blade measurement integration structure of claim 1,
each sensing part (4) is in threaded connection with the corresponding lead hole.
7. The stator blade measurement integration structure of claim 1,
the stator blade (1) is provided with an upper shaft neck (5) on a blade crown; the upper journal (5) is provided with a lead channel; one end of the lead channel is communicated with the bundling channel, and the other end of the lead channel extends to the end face, back to the stator blade (1), of the upper shaft neck (5).
8. The stator blade measurement integration structure of claim 7,
the stator blade (1) is provided with a lower journal (6) on the blade root.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010439683.6A CN111561478A (en) | 2020-05-22 | 2020-05-22 | Stator blade measurement integrated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010439683.6A CN111561478A (en) | 2020-05-22 | 2020-05-22 | Stator blade measurement integrated structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111561478A true CN111561478A (en) | 2020-08-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010439683.6A Pending CN111561478A (en) | 2020-05-22 | 2020-05-22 | Stator blade measurement integrated structure |
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| Country | Link |
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| CN (1) | CN111561478A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114320981A (en) * | 2021-12-06 | 2022-04-12 | 中国航发沈阳发动机研究所 | Total pressure measurement sensing part and compressor interstage total pressure measurement structure thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080025839A1 (en) * | 2006-07-31 | 2008-01-31 | Jan Christopher Schilling | Stator vane and gas turbine engine assembly including same |
| 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 |
| CN106918410A (en) * | 2017-03-29 | 2017-07-04 | 北京航空航天大学 | A kind of stagnation temperature blade profile probe |
| 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 |
| CN207195266U (en) * | 2017-09-13 | 2018-04-06 | 中国航发沈阳发动机研究所 | Stagnation temperature probe between compressor stage |
| CN109141900A (en) * | 2018-07-25 | 2019-01-04 | 中国航发沈阳发动机研究所 | A kind of probe measuring rotor outlet air-flow angle |
| CN110735806A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | stator blade measuring structure |
-
2020
- 2020-05-22 CN CN202010439683.6A patent/CN111561478A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080025839A1 (en) * | 2006-07-31 | 2008-01-31 | Jan Christopher Schilling | Stator vane and gas turbine engine assembly including same |
| 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 |
| CN106918410A (en) * | 2017-03-29 | 2017-07-04 | 北京航空航天大学 | A kind of stagnation temperature blade profile probe |
| CN207195266U (en) * | 2017-09-13 | 2018-04-06 | 中国航发沈阳发动机研究所 | Stagnation temperature probe between compressor stage |
| 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 |
| CN109141900A (en) * | 2018-07-25 | 2019-01-04 | 中国航发沈阳发动机研究所 | A kind of probe measuring rotor outlet air-flow angle |
| CN110735806A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | stator blade measuring structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114320981A (en) * | 2021-12-06 | 2022-04-12 | 中国航发沈阳发动机研究所 | Total pressure measurement sensing part and compressor interstage total pressure measurement structure thereof |
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Application publication date: 20200821 |