CN109098997A - A kind of compressor passage aerodynamic parameter measurement method - Google Patents
A kind of compressor passage aerodynamic parameter measurement method Download PDFInfo
- Publication number
- CN109098997A CN109098997A CN201810797906.9A CN201810797906A CN109098997A CN 109098997 A CN109098997 A CN 109098997A CN 201810797906 A CN201810797906 A CN 201810797906A CN 109098997 A CN109098997 A CN 109098997A
- Authority
- CN
- China
- Prior art keywords
- measurement
- compressor
- lead channels
- lead
- blade
- 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.)
- Pending
Links
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to compressor design field, in particular to a kind of compressor passage aerodynamic parameter measurement method.The measurement method, comprising the following steps: Step 1: opening up lead channels, lead channels extend from the outer shaft of compressor stator blade to inner shaft；Step 2: opening up several Measurement channels, Measurement channel is opened up in predetermined altitude, and is connected to lead channels and compressor passage；Step 3: several test lead measurement ends are sequentially passed through lead channels and Measurement channel, the other end is connect with test equipment；Step 4: being measured to compressor passage aerodynamic parameter.Test lead is arranged in lead channels and Measurement channel this method, easy to fall off the problems in compressor passage so as to avoid rod-shaped sensor in existing measurement method, stable structure, high reliablity；In addition, this method relates generally to the improvement to compressor stator blade, and can retain stator blade position and type face, still have certain guide functions, the influence to aerodynamic parameter is smaller.
Description
Technical field
The present invention relates to compressor design field, in particular to a kind of compressor passage aerodynamic parameter measurement method.
Background technique
In the design phase of compressor, the aerodynamic parameter of different location in its runner is obtained, can be blade aerodynamic type face, spy
The bleed design at different position provides support, in addition it is also possible to as the input for obturaging design between compressor rotor, stator.
Aerodynamic parameter at compressor outside wall surface is measured, can directly be punched on casing, by sensor
Outside wall surface is fixed on to measure, and measurement position is in the middle part of the runner or close to runner inner wall face, the measurement of aerodynamic parameter
More difficult implementation.
Currently, for being measured in the middle part of runner or close to aerodynamic parameter at runner inner wall face, the side generallyd use
Method is that rod-shaped sensor will be extend into runner, is directly measured, such measurement method is restricted to built-in length, and bar
Shape passes sensor as cantilever setting, can have an impact to runner interior air-flow, easy to fall off when working at the same time, and influences the accurate of measurement
Property.
Summary of the invention
The object of the present invention is to provide a kind of compressor passage aerodynamic parameter measurement method, with overcome or alleviated by it is above-mentioned extremely
The problem of few one side.
The technical scheme is that a kind of compressor passage aerodynamic parameter measurement method, comprising the following steps:
Step 1: opening up lead channels, lead channels extend from the outer shaft of compressor stator blade to inner shaft；
Step 2: opening up several Measurement channels, Measurement channel is opened up in predetermined altitude, and is connected to lead channels and compressor
Runner；
Step 3: several test lead measurement ends are sequentially passed through lead channels and Measurement channel, the other end and survey
Try equipment connection；
Step 4: being measured to compressor passage aerodynamic parameter.
It preferably, further include that Intensity Design is carried out to stator blade 5 in above-mentioned measurement method, so that stator blade 5 is being opened
If meeting intensity requirement after lead channels and Measurement channel.
Preferably, above-mentioned Intensity Design includes carrying out thickening design to stator blade 5.Stator blade 5 thicken and is set
After meter, the distance of outside wall surface to lead channels and Measurement channel inner wall is not less than 6mm.
Preferably, lead channels open up on the blade of compressor stator blade in step 1, lead to when carrying out step 4
It crosses rocker arm connection and the angle of compressor stator blade is adjusted in linkage ring.
Preferably, lead channels extend to inner shaft 5c in design procedure one；In step 2 Measurement channel along stator inner ring 6 and
Inner shaft radially opens up.
The present invention has the advantages that providing a kind of compressor passage aerodynamic parameter measurement method, this method is by opening
If lead channels and Measurement channel, and test lead is disposed therein, so as to avoid rod-shaped sensing in existing measurement method
Device is easy to fall off the problems in compressor passage, stable structure, high reliablity；It opens up multiple Measurement channels and can measure simultaneously
Multiple parameters are independent of each other, and multiple channels are realized on a blade, can reduce the influence to whole grade blade.In addition, should
Method relates generally to the improvement to compressor stator blade, and can retain stator blade position and type face, still has certain lead
Stream effect, the influence to aerodynamic parameter are smaller.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for implementing compressor passage aerodynamic parameter measurement method of the present invention.
Fig. 2 is the structural schematic diagram of stator blade in Fig. 1.
Appended drawing reference:
1, casing；2, rotor disk；3, preceding rotor blade；4, rear rotor blade；5, stator blade；6, stator inner ring；7, solid
Determine nut；8, rocker arm；9 linkage rings；10 test leads；11, comb tooth；5a, blade；5b, outer shaft；5c, inner shaft.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
1-2 is described in further details the present invention with reference to the accompanying drawing.
As shown in Figure 1,4 two-stage rotor blade of preceding rotor blade 3 and rear rotor blade is installed on compressor rotor disk 2,
Stator blade 5 is between rotor blade 3 and rear rotor blade 4；Comb tooth 11 is arranged on rotor disk 2, in stator inner ring 6
Honeycomb cooperatively forms seal structure, prevents air-flow from passing through.
As shown in Fig. 2, stator blade 5 includes blade 5a, outer shaft 5b, tri- parts inner shaft 5c, wherein blade outer shaft 5b is worn
It crosses casing 1 shown in Fig. 1 to couple with rocker arm 8, under the drive of linkage ring 9, the angle of stator blade 5 can be adjusted
Section；Inner shaft 5c is worn into stator inner ring 6 shown in Fig. 1, and is fixed by stator inner ring 6.
A kind of compressor passage aerodynamic parameter measurement method of the present invention, comprising the following steps:
Step 1: opening up lead channels, lead channels extend from the outer shaft 5b of compressor stator blade 5 to inner shaft 5c；
Step 2: open it is several set Measurement channel, Measurement channel is opened up in predetermined altitude, and is connected to lead channels and compressor
Runner；
Step 3: several test lead measurement ends are sequentially passed through lead channels and Measurement channel, the other end and survey
Try equipment connection；
Step 4: being measured to compressor passage aerodynamic parameter.
Further, Intensity Design is carried out to stator blade 5, so that stator blade 5 is opening up lead channels and measuring logical
Meet intensity requirement behind road.Intensity Design may include carrying out thickening design to stator blade 5.Stator blade 5 is thickeied
After design, the distance of outside wall surface to lead channels and Measurement channel inner wall is not less than 0.6mm.
Further, lead channels open up on the blade of compressor stator blade 5 in above-mentioned measurement method step 1,
Coupled when step 4 by rocker arm 8 and the angle of compressor stator blade 5 is adjusted in the ring 9 that links.In test process
The middle controllability using the angle of stator blade 5 itself influences original structure small.
Further, lead channels extend to inner shaft 5c in above-mentioned measurement method step 1；Measurement channel edge in step 2
Stator inner ring 6 and inner shaft radially open up, and can measure to 6 liang of side cavity's aerodynamic parameters of stator inner ring, at this are measurement at this
The key position of amount, air-flow is relatively stable to can get preferable measurement effect.
The above-mentioned quantity for being understandable that Measurement channel and test lead can be by related technical personnel according to measurement needs
It is determined, may be selected to be 3 herein, and be distributed in the position of upper, middle and lower three of stator blade 5.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (5)
1. a kind of compressor passage aerodynamic parameter measurement method, which comprises the following steps:
Step 1: opening up lead channels, the lead channels are prolonged from the outer shaft (5b) of compressor stator blade (5) to inner shaft (5c)
It stretches；
Step 2: opening up several Measurement channels, the Measurement channel is opened up in predetermined altitude, and is connected to the lead channels and pressure
Mechanism of qi runner；
Step 3: several test lead measurement ends are sequentially passed through the lead channels and the Measurement channel, the other end
It is connect with test equipment；
Step 4: being measured to compressor passage aerodynamic parameter.
2. measurement method according to claim 1, which is characterized in that carry out thickening to the stator blade (5) and set
Meter, so that the stator blade (5) meets intensity requirement after opening up the lead channels and the Measurement channel.
3. measurement method according to claim 2, which is characterized in that after the stator blade (5) carries out thickening design,
Outside wall surface to the lead channels and the distance of the Measurement channel inner wall are not less than 0.6mm.
4. measurement method according to claim 1, which is characterized in that lead channels are in Profile For Compressor Stator described in step 1
It is opened up on the blade of blade (5), coupled when carrying out step 4 by rocker arm (8) and links ring (9) to the Profile For Compressor Stator
The angle of blade (5) is adjusted.
5. measurement method according to claim 1, it is characterised in that:
Lead channels described in step 1 extend to the inner shaft (5c)；
Measurement channel described in step 2 is radially opened up along stator inner ring (6) and the inner shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810797906.9A CN109098997A (en) | 2018-07-19 | 2018-07-19 | A kind of compressor passage aerodynamic parameter measurement method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810797906.9A CN109098997A (en) | 2018-07-19 | 2018-07-19 | A kind of compressor passage aerodynamic parameter measurement method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109098997A true CN109098997A (en) | 2018-12-28 |
Family
ID=64846687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810797906.9A Pending CN109098997A (en) | 2018-07-19 | 2018-07-19 | A kind of compressor passage aerodynamic parameter measurement method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109098997A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110735806A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | stator blade measuring structure |
| CN111472998A (en) * | 2020-04-21 | 2020-07-31 | 中国航发沈阳发动机研究所 | Compressor inner flow passage surface static pressure test stator blade structure |
Citations (3)
| 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 |
| US20110218741A1 (en) * | 2008-10-14 | 2011-09-08 | Hitachi, Ltd. | Device for Detecting Defect of Turbine Rotor Blade and Method for Detecting Defect of Turbine Rotor 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 |
-
2018
- 2018-07-19 CN CN201810797906.9A patent/CN109098997A/en active Pending
Patent Citations (3)
| 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 |
| US20110218741A1 (en) * | 2008-10-14 | 2011-09-08 | Hitachi, Ltd. | Device for Detecting Defect of Turbine Rotor Blade and Method for Detecting Defect of Turbine Rotor 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 |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110735806A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | stator blade measuring structure |
| CN111472998A (en) * | 2020-04-21 | 2020-07-31 | 中国航发沈阳发动机研究所 | Compressor inner flow passage surface static pressure test stator blade structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109098997A (en) | A kind of compressor passage aerodynamic parameter measurement method | |
| CN104950788B (en) | Regular loading truck control system and quantifying and loading instrument | |
| EP2369314A1 (en) | Rotating blade analysis | |
| US20080030073A1 (en) | The determination of runway landing conditions | |
| CN104296714A (en) | Method for measuring tip clearance of turbine concave cavity blades | |
| EP2409028A2 (en) | Wind turbine blade control | |
| Stadtmüller et al. | Experimental and numerical investigation of wake-induced transition on a highly loaded LP turbine at low Reynolds numbers | |
| Solomon | Unsteady boundary layer transition on axial compressor blades | |
| CN105716837A (en) | Airborne rotor motion measurement method based on PSD optical imaging | |
| CN104068839B (en) | sphygmomanometer | |
| CN105074224B (en) | The oily connector of rotation with center line mount type displacement probe, the system and method for measuring the displacement of the regulating system of variable pitch axial flow blower | |
| CN109084907A (en) | A kind of leaf total temperature probe for Interstage Turbine Temperature measurement | |
| US10703503B2 (en) | Method of displaying data in an aircraft | |
| CN106932139A (en) | A kind of four pore pressure force blade profile probes | |
| CN110374754A (en) | System and vehicle are protected in fault detection | |
| CN106840513A (en) | A kind of stagnation pressure blade profile probe | |
| CN106338399B (en) | A kind of calculation method across the total static probe measurement true value of supersonic speed | |
| CN205909970U (en) | Pressure testing device | |
| CN108197342A (en) | A kind of non-design gas leakage computational methods of aero-engine air system | |
| CN107907232A (en) | For measuring the temperature pressure combinations probe of turbomachinery interior flow field | |
| CN110967182B (en) | Cone crusher vibration data acquisition and preprocessing method | |
| CN207763763U (en) | Air cleaner flow measuring structure and engine assembly | |
| CN204007806U (en) | Mechanical meters flow verification system | |
| DRELA | Viscous and inviscid inverse schemes using Newton's method | |
| CN109542215A (en) | Safety cap wears monitoring method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181228 |
|
| RJ01 | Rejection of invention patent application after publication |