CN113063598A - Thrust measurement structure and measurement method for spray pipe - Google Patents
Thrust measurement structure and measurement method for spray pipe Download PDFInfo
- Publication number
- CN113063598A CN113063598A CN202110291317.5A CN202110291317A CN113063598A CN 113063598 A CN113063598 A CN 113063598A CN 202110291317 A CN202110291317 A CN 202110291317A CN 113063598 A CN113063598 A CN 113063598A
- Authority
- CN
- China
- Prior art keywords
- sealing
- air inlet
- thrust
- ring
- semi
- 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.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The application provides a spray tube thrust measurement structure, includes: the comb tooth gap air inlet structure is used for measuring thrust of a spray pipe and comprises a sealing ring with a plurality of comb teeth, a first pressing ring used for pressing the sealing ring to an air inlet channel and a comb tooth fixing bolt used for connecting the first pressing ring with the air inlet channel, wherein the sealing ring is provided with a pressure taking hole located on the outer side of the comb tooth, the pressure taking pipe is communicated with the pressure taking hole, one side of the sealing ring, facing the air inlet channel, is provided with a sealing pad groove, and a flexible sealing pad is arranged in the sealing pad groove; and the grate gap blocking structure is used for blocking the grate gap air inlet structure and comprises a semi-ring type sealing hoop, a sealing hoop bolt used for connecting the semi-ring type sealing hoop and a second pressing plate for pressing the semi-ring type sealing hoop, wherein the second pressing plate is connected to the air inlet channel through the sealing connecting bolt, the semi-ring type sealing hoop is provided with at least one sealing groove, and a sealing ring is arranged in the sealing groove.
Description
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a thrust measurement structure and a thrust measurement method for a spray pipe.
Background
When an aircraft engine spray pipe test is carried out, the thrust of the spray pipe needs to be measured. The measurement is usually carried out by using a force measuring platform or a force measuring balance, and during the measurement, the air is introduced into the engine through a special air inlet device, and the air inlet device and the engine are generally in a contact structure and a non-contact structure.
The contact type air inlet structure generally adopts a flexible connection mode, however, the flexible connection has the defects of difficult quantitative calculation and irremovable force measurement interference, and the force measurement precision is influenced; the non-contact type air inlet structure usually adopts an air inlet mode with a sealing structure, however, the air inlet mode with the sealing structure needs a method of calibrating the leakage amount of the grate by using a standard sonic nozzle to solve the problem of measuring the gas leakage amount at the grate, the leakage amount of the grate is unstable, the flow state calibrated by the leakage amount is different from the flow state in a test, the pressure field is not completely the same, and a certain error also exists.
Disclosure of Invention
The present application is directed to a nozzle thrust measurement structure and method for solving or reducing at least one of the problems of the related art.
In one aspect, the present application provides a nozzle thrust measurement structure, including:
the comb tooth gap air inlet structure is used for measuring thrust of a spray pipe and comprises a sealing ring with a plurality of comb teeth, a first pressing ring used for pressing the sealing ring to an air inlet channel and a comb tooth fixing bolt used for connecting the first pressing ring with the air inlet channel, wherein the sealing ring is provided with a pressure taking hole located on the outer side of the comb tooth, the pressure taking pipe is communicated with the pressure taking hole, one side of the sealing ring, facing the air inlet channel, is provided with a sealing pad groove, and a flexible sealing pad is arranged in the sealing pad groove; and
a labyrinth clearance block structure for shutoff labyrinth clearance inlet structure, labyrinth clearance block structure includes semi-ring type seal hoop, is used for connecting semi-ring type seal hoop's seal hoop bolt and pressure and holds semi-ring type seal hoop's second clamp plate, the second clamp plate pass through sealing connection bolted connection to on the intake duct, wherein, semi-ring type seal hoop has at least one seal groove, set up the sealing washer in the seal groove.
Furthermore, the comb tooth is of a right-angled triangle structure, and the right-angled edge of the comb tooth is positioned on one side close to the air inlet channel.
Furthermore, the number of the grid teeth in the sealing ring is not less than three.
Furthermore, the pressure measuring hole is positioned on the outer side of the grate tooth closest to the air inlet channel in the plurality of grate teeth.
Furthermore, the flexible sealing gasket is made of fluoroplastic materials.
Furthermore, the distance between the grate teeth of the sealing ring and the main runner is 1 mm-2 mm.
Furthermore, the sealing gasket groove on the sealing ring and the sealing groove on the semi-ring type sealing hoop are rectangular grooves.
Furthermore, the number of the sealing grooves on the semi-ring type sealing hoop is two.
In another aspect, the present application provides a nozzle thrust measurement method, which uses the above nozzle thrust measurement structure, and the measurement method includes:
firstly, connecting a main runner and an air inlet channel through a labyrinth clearance plugging structure, and carrying out a flow performance test on an engine test piece to obtain a flow test result;
then, connecting the main runner with the air inlet channel through a grate gap air inlet structure, and carrying out a thrust test on an engine test piece to obtain a thrust test result;
and finally, correcting the thrust test result of the thrust test according to the flow test result of the flow performance test to obtain the corrected thrust test result.
Further, the correction formula is:
in the formula, m1、Pt1、Tt1Respectively mass flow, pressure and temperature in the flow test results, P't1、T′t1Respectively being the pressure and temperature m 'in the thrust test results'1The mass flow after correction for the thrust test.
The thrust measuring structure and the measuring method of the spray pipe can solve the problems that when the thrust of the spray pipe is measured, the flow measurement is inaccurate due to non-contact sealing, and the thrust and the flow of the spray pipe cannot be accurately measured by air entraining.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a general schematic view of a grate gap air inlet structure in the application.
Fig. 2 is a partially enlarged view of a grate gap air inlet structure in the present application.
Fig. 3 is a schematic view of a plugging structure of a grate gap in the present application.
Reference numerals:
11-Main flow channel
12-inlet duct
20-grate gap air inlet structure
21-sealing ring, 211-grid tooth, 212-pressure-taking hole
22-first pressure ring
23-pressure tapping pipe
24-Flexible gasket
25-grid tooth fixing bolt
30-comb tooth gap plugging structure
31-semi-ring type sealing hoop
32-seal hoop bolt
33-sealing ring
34-second pressure ring
35-sealing connecting bolt
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve the thrust measurement of the spray pipe in the prior art, the problem that the flow measurement is inaccurate due to non-contact sealing and the thrust and the flow of the bleed air can not accurately measure the spray pipe is provided.
As shown in fig. 1 to 3, the thrust measuring structure of the nozzle mainly includes two structures, one is a labyrinth gap air inlet structure 20, and the other is a labyrinth gap blocking structure 30.
The labyrinth gap air inlet structure 20 mainly comprises a sealing ring 21, a first pressing ring 22 and a labyrinth fixing bolt 25, wherein the sealing ring 21 is provided with a plurality of labyrinth teeth 211, the outer side of the labyrinth teeth 211 is provided with a pressure taking hole 212, the sampling pipe 23 penetrates through the first pressing ring 22 to be communicated with the pressure taking hole 212 to realize gap pressure measurement, one side of the sealing ring 21 facing the air inlet channel 12 is provided with a sealing gasket groove, a flexible sealing gasket 24 is arranged in the sealing gasket groove, the first pressing ring 22 presses and holds the sealing ring 21 provided with the flexible sealing gasket 24 on the air inlet channel 12, and the sealing ring 21 is fixed through the labyrinth fixing bolt 25.
The grate gap plugging structure 30 for plugging the grate gap can eliminate errors caused by the inconsistency of the flow fields in the calibration flow state and the test state. The labyrinth gap plugging structure 30 comprises a semi-ring type sealing hoop 31, a sealing hoop bolt 32 for connecting the semi-ring type sealing hoop 31 and a second pressure plate 34 for pressing and holding the semi-ring type sealing hoop 31, wherein the second pressure plate 34 is connected to the air inlet channel 12 through a sealing connecting bolt 35, the semi-ring type sealing hoop 31 is provided with at least one sealing groove, and a sealing ring 33 is arranged in the sealing groove.
In the preferred embodiment of the present application, the grate 211 is a right-angled triangle structure, and the right-angled side of the grate 211 is located at the side close to the air inlet 12, so that the internal air flow can be better blocked.
In the preferred scheme of the above embodiment, the number of the grid teeth 211 in the sealing ring 21 is not less than three, so that a better sealing effect can be achieved.
In addition, in the above embodiment, the pressure taking hole 212 is located outside the labyrinth closest to the air inlet 12 among the plurality of the labyrinth 32, so that the air pressure can be measured to the maximum.
In the above embodiments of the present application, the flexible sealing pad 24 may be made of fluoroplastic material, which has certain flexibility and is wear-resistant and non-slip.
Allowing for clearance control and minimal gas leakage. In the present application, the distance between the comb tooth 211 of the sealing ring 21 and the main flow passage 11 is 1mm to 2mm, for example, in one embodiment, the gap is 1 mm. Through the combination of the gaps and the plurality of grid teeth 211, the pressure attenuation of leaked gas is increased, and the purpose of reducing the leakage amount can be achieved.
Further, the sealing gasket groove on the sealing ring 21 and the sealing groove on the semi-ring type sealing hoop 31 are both rectangular grooves.
In the above embodiment, the number of the sealing grooves of the half-ring type sealing band 31 is preferably two.
Finally, the application also provides a thrust measurement method of the spray pipe, the thrust measurement structure of the spray pipe is adopted, and the thrust measurement method comprises the following steps:
firstly, a main flow channel (11) and an air inlet channel (12) are connected through a labyrinth clearance plugging structure (30), a flow performance test of a generator test piece is carried out, a flow test result is obtained, during the flow performance test, the labyrinth clearance plugging is realized, and the interference of unstable labyrinth leakage on the actual flow of a measuring nozzle can be eliminated;
connecting the main runner (11) and the air inlet (12) through the grate gap air inlet structure (20), and performing a thrust test on an engine test piece to obtain a thrust test result;
and fitting a relation curve of the flow and the inlet pressure and temperature of the test piece through a flow test, and further correcting the actual flow of the thrust test (with the grate) spray pipe.
CorrectionThe formula is as follows:
in the formula, m1、Pt1、Tt1Respectively mass flow, pressure and temperature in the flow test results, P't1、T′t1Respectively being the pressure and temperature m 'in the thrust test results'1The mass flow after correction for the thrust test.
According to the thrust measuring device and method for the spray pipe, firstly, a non-contact air inlet structure is adopted, so that force measuring interference caused by a flexible air inlet structure is eliminated, and force measuring precision is provided; then, a 'plugging labyrinth clearance test method' is adopted, the inlet flow of the spray pipe is obtained through test fitting, the problem of flow measurement fluctuation is solved, and the flow measurement precision is improved; the grid tooth gap plugging structure can achieve the target of zero discharge, avoid replacing a test pipeline, reduce the workload, achieve the target of accurate measurement of the flow of the spray pipe and no interference of leakage, and has compact and efficient structure, and is convenient for the thrust and flow measurement of the spray pipe.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A nozzle thrust measurement structure, comprising:
the comb tooth gap air inlet structure (20) is used for measuring thrust of the spray pipe, the comb tooth gap air inlet structure (20) comprises a sealing ring (21) with a plurality of comb teeth (211), a first pressing ring (22) used for pressing the sealing ring (21) to the air inlet channel (12) and a comb tooth fixing bolt (25) used for connecting the first pressing ring (22) with the air inlet channel (12), wherein the sealing ring (21) is provided with a pressure taking hole (212) located on the outer side of the comb teeth (211), the pressure taking pipe (23) is communicated with the pressure taking hole (212), one side, facing the air inlet channel (12), of the sealing ring (21) is provided with a sealing gasket groove, and a flexible sealing gasket (24) is arranged in the sealing gasket groove; and
a labyrinth clearance shutoff structure (30) for shutoff labyrinth clearance inlet structure (20), labyrinth clearance shutoff structure (30) include semi-ring type seal hoop (31), be used for connecting seal hoop bolt (32) and the pressure of semi-ring type seal hoop (31) hold second clamp plate (34) of semi-ring type seal hoop (31), second clamp plate (34) are connected to through sealed connecting bolt (35) on intake duct (12), wherein, semi-ring type seal hoop (31) have at least one seal groove, set up sealing washer (33) in the seal groove.
2. The nozzle thrust measuring structure according to claim 1, wherein the comb tooth (211) is in a right-angled triangle structure, and a right-angled side of the comb tooth (211) is positioned on one side close to the air inlet (12).
3. Nozzle thrust measurement arrangement according to claim 1 or 2, characterized in that the number of the grates (211) in the sealing ring (21) is not less than three.
4. The nozzle thrust measurement structure of claim 3, wherein the pressure tapping hole (212) is located outside a labyrinth of the plurality of grates (32) closest to the inlet duct (12).
5. Nozzle thrust measurement arrangement according to claim 1, characterized in that the flexible sealing gasket (24) is made of fluoroplastic material.
6. The nozzle thrust measurement structure according to claim 1, characterized in that the distance between the comb tooth (211) of the sealing ring (21) and the main flow channel (11) is 1mm to 2 mm.
7. The nozzle thrust measurement arrangement of claim 1, wherein the gasket groove on the sealing ring (21) and the sealing groove on the semi-annular sealing band (31) are rectangular grooves.
8. Nozzle thrust measurement arrangement according to claim 1 or 7, characterized in that the number of sealing grooves on the semi-annular sealing band (31) is two.
9. A nozzle thrust measurement method, characterized by using the nozzle thrust measurement structure of any one of claims 1 to 8, the measurement method comprising:
firstly, connecting a main flow channel (11) and an air inlet channel (12) through a labyrinth clearance plugging structure (30), and carrying out a flow performance test on an engine test piece to obtain a flow test result;
then, connecting the main flow passage (11) with the air inlet passage (12) through the grate gap air inlet structure (20), and carrying out a thrust test on an engine test piece to obtain a thrust test result;
and finally, correcting the thrust test result of the thrust test according to the flow test result of the flow performance test to obtain the corrected thrust test result.
10. The nozzle thrust measurement method of claim 9, wherein the correction formula is:
in the formula, m1、Pt1、Tt1Respectively mass flow, pressure and temperature in the flow test results, P't1、T′t1Respectively being the pressure and temperature m 'in the thrust test results'1The mass flow after correction for the thrust test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110291317.5A CN113063598B (en) | 2021-03-18 | 2021-03-18 | Thrust measurement structure and measurement method for spray pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110291317.5A CN113063598B (en) | 2021-03-18 | 2021-03-18 | Thrust measurement structure and measurement method for spray pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113063598A true CN113063598A (en) | 2021-07-02 |
| CN113063598B CN113063598B (en) | 2022-10-28 |
Family
ID=76562021
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110291317.5A Active CN113063598B (en) | 2021-03-18 | 2021-03-18 | Thrust measurement structure and measurement method for spray pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113063598B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140133963A1 (en) * | 2012-11-12 | 2014-05-15 | Rolls-Royce Plc | Apparatus and method for measuring gas flow through a rotary seal |
| CN104047640A (en) * | 2014-06-10 | 2014-09-17 | 清华大学 | Brush type sealing structure with adjustable radial clearance |
| CN204476820U (en) * | 2014-12-08 | 2015-07-15 | 开封天宸能源化工机械有限公司 | Super-flow combined type centrifugal air compressor |
| CN106194278A (en) * | 2016-07-29 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of gas-turbine unit densification device |
| CN205940952U (en) * | 2016-08-15 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Advance gas seal device |
| CN208397474U (en) * | 2018-06-14 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of airflow line sealing structure |
| CN209129687U (en) * | 2018-12-12 | 2019-07-19 | 中国航发沈阳发动机研究所 | The seal structure of double bleeds |
-
2021
- 2021-03-18 CN CN202110291317.5A patent/CN113063598B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140133963A1 (en) * | 2012-11-12 | 2014-05-15 | Rolls-Royce Plc | Apparatus and method for measuring gas flow through a rotary seal |
| CN104047640A (en) * | 2014-06-10 | 2014-09-17 | 清华大学 | Brush type sealing structure with adjustable radial clearance |
| CN204476820U (en) * | 2014-12-08 | 2015-07-15 | 开封天宸能源化工机械有限公司 | Super-flow combined type centrifugal air compressor |
| CN106194278A (en) * | 2016-07-29 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of gas-turbine unit densification device |
| CN205940952U (en) * | 2016-08-15 | 2017-02-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Advance gas seal device |
| CN208397474U (en) * | 2018-06-14 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of airflow line sealing structure |
| CN209129687U (en) * | 2018-12-12 | 2019-07-19 | 中国航发沈阳发动机研究所 | The seal structure of double bleeds |
Non-Patent Citations (2)
| Title |
|---|
| 缪文静、王锁芳: "台阶式篦齿封严特性的数值模拟", 《南京师范大学学报(工程技术版)》 * |
| 魏勇: "某小型涡扇发动机性能试验技术研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113063598B (en) | 2022-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7819578B2 (en) | Fluid temperature measurement device | |
| CN112067304B (en) | Method for measuring inlet flow of compressor in engine whole machine test | |
| CN112945443B (en) | Jet pipe thrust measurement platform | |
| CN111044252A (en) | High-precision air inlet channel flow measuring method | |
| CN113063598B (en) | Thrust measurement structure and measurement method for spray pipe | |
| CN110454574B (en) | Coaxial air inlet sealing device with inner culvert and outer culvert for measuring thrust device | |
| CN115014647A (en) | Corrugated pipe reliability verification test device | |
| US5517852A (en) | Diagnostic performance testing for gas turbine engines | |
| CN109738193B (en) | Air-cooled measuring section structure for gas turbine combustion chamber test | |
| CN115901268A (en) | Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine | |
| US20170051682A1 (en) | System and method for abatement of dynamic property changes with proactive diagnostics and conditioning | |
| CN115356115B (en) | Layout method for mainstream flow field fine test in core machine environment | |
| CN115356027A (en) | High-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance | |
| US20160053767A1 (en) | Inlet bellmouth with coating in measurement annulus region | |
| CN110656984A (en) | Device and method for measuring airflow at outlet of disk edge position of turbine disk | |
| CN208397474U (en) | A kind of airflow line sealing structure | |
| CN110454275B (en) | Independent measuring structure for air leakage of compressor end and turbine end of turbocharger | |
| CN112840180B (en) | Method and device for calculating venturi tube pressure | |
| US6694728B2 (en) | Exhaust gas dilution apparatus | |
| CN106885683B (en) | Hemispherical head twelve-hole steady-state pressure probe for measuring three-dimensional complex flow field | |
| CN110702307A (en) | Method for testing pressure parameters of multi-channel sensor | |
| CN220487751U (en) | High-precision comprehensive performance testing system for high-flow injection valve | |
| KR20090067270A (en) | Pipe connecting unit for engine test apparatus and engine test apparatus having the same | |
| CN219348180U (en) | Engine gas circuit pressure distribution simulation platform | |
| CN215374470U (en) | Measure test device of tenon assembly structure flow coefficient |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |