CN112362350A - Special blanking cover for T2 measurement of aircraft engine - Google Patents
Special blanking cover for T2 measurement of aircraft engine Download PDFInfo
- Publication number
- CN112362350A CN112362350A CN202011037399.2A CN202011037399A CN112362350A CN 112362350 A CN112362350 A CN 112362350A CN 202011037399 A CN202011037399 A CN 202011037399A CN 112362350 A CN112362350 A CN 112362350A
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- China
- Prior art keywords
- screw
- engine
- cover plate
- limiting disc
- screws
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- 238000005259 measurement Methods 0.000 title claims description 10
- 230000000903 blocking effect Effects 0.000 claims abstract description 13
- 239000000446 fuel Substances 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- G01M15/02—Details or accessories of testing apparatus
-
- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a special blanking cover for measuring T2 of an aeroengine, which comprises: the device comprises an operating rod, a handle, a screw limiting disc, a blocking cover plate, two screws and two nuts; the handle is arranged at the upper end of the operating rod, the screw limiting disc and the blocking cover plate are arranged up and down and are correspondingly in threaded connection with the lower portion of the operating rod, two through holes are correspondingly formed in the screw limiting disc and the blocking cover plate, the two screws correspondingly penetrate through the through holes in the screw limiting disc and the blocking cover plate and are matched with nuts, and the nuts are limited between the screw limiting disc and the blocking cover plate, so that the screws are prevented from falling off. The invention can complete the replacement of the plugging cover and the T2 thermocouple without stopping the engine in the test run, reduce the starting times of the engine, avoid increasing the cooling and heating time of the engine, reduce the fuel consumption of the engine in the test run and save the test run cost.
Description
Technical Field
The invention belongs to the field of plug covers for measuring the temperature of an aeroengine, and particularly provides a special plug cover for measuring T2 of the aeroengine.
Background
In some aircraft engine test recording performances, the driving state needs to detach the plug cover on the compressor casing of the engine, and then a temperature sensor (namely a T2 thermocouple is installed) is installed to measure the temperature (T2 temperature) after the compressor, so as to calculate the engine performances, wherein the adopted casing plug cover and screws are shown in figure 1. When the engine is in a driving state, the high-pressure compressor is heated, the temperature of the casing plug cover and the screw is very high, and an operator cannot detach the screw and the casing plug cover from the engine. The traditional operation method comprises the steps that an engine needs to be stopped, after a casing is cooled, a screw and a casing blocking cover are removed, a T2 thermocouple is installed, after the performance of driving and recording is achieved, the engine is cooled and stopped, and then the screw and the casing blocking cover are restored to the original state of the engine, and the follow-up test run content is completed. Such an operation procedure causes an increase in the trial cost, an increase in the trial time of the engine, an increase in the number of 2 starts, and an increase in the engine operating time of 20 minutes.
Disclosure of Invention
The invention aims to provide a special plug for measuring T2 of an aircraft engine, which can finish the installation or disassembly work within a short time (within 5 minutes), and solves the problem that the plug cannot be installed or disassembled under severe environments such as high temperature, high pressure, vibration and the like during the engine test.
The technical scheme of the invention is as follows: a specialized closure for use in an aircraft engine T2 measurement, comprising: the device comprises an operating rod 1, a handle 2, a screw limiting disc 3, a blocking cover plate 4, two screws 5 and two nuts 6; handle 2 locates 1 upper end of action bars, arrange about screw spacing dish 3 and blanking cover plate 4, correspond threaded connection in 1 lower part of action bars, all correspond on screw spacing dish 3 and the blanking cover plate 4 and be equipped with two through-holes, two screws 5 correspond the through-hole that passes on screw spacing dish 3 and the blanking cover plate 4 and cooperate and have nut 6, nut 6 is spacing between screw spacing dish 3 and blanking cover plate 4 to prevent that screw 5 from droing.
Further, the shape and size of the screw limiting disc 3 are consistent with those of the blocking cover plate 4.
Further, the handle 2 is circular ring shaped.
Further, the screw 5 is an M5 × 1.0 screw.
The invention has the following beneficial effects:
the invention can complete the replacement of the plugging cover and the T2 thermocouple without stopping the engine in the test run, reduce the starting times of the engine, avoid increasing the cooling and heating time of the engine, reduce the fuel consumption of the engine in the test run and save the test run cost.
Drawings
FIG. 1 is a schematic view of a prior art plugging cover structure;
FIG. 2 is a front view of the present invention;
FIG. 3 is a top view of the present invention;
FIG. 4 is a side view of the present invention;
in the figure: 1. an operating lever; 2. a handle; 3. a screw limiting disc; 4. blocking the cover plate; 5. a screw; 6. And a nut.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
2-4, a specialized closure for use in the measurement of aircraft engine T2, comprising: the device comprises an operating rod 1, a handle 2, a screw limiting disc 3, a blocking cover plate 4, two screws 5 and two nuts 6; handle 2 locates 1 upper end of action bars, and the spacing dish of screw 3 and blanking cover plate 4 are arranged from top to bottom, correspond threaded connection in 1 lower part of action bars, all correspond on spacing dish of screw 3 and the blanking cover plate 4 and be equipped with two through-holes, and two screw 5 correspond the through-hole that passes on spacing dish of screw 3 and the blanking cover plate 4 and cooperate and have nut 6, and nut 6 is spacing between spacing dish of screw 3 and blanking cover plate 4 to prevent that screw 5 from droing.
In the embodiment of the invention, the screw limiting disc 3 and the blocking cover plate 4 are consistent in shape and size.
In the embodiment of the invention, the handle 2 is in a circular ring shape, so that the handle is convenient to hold by hands.
In the embodiment of the invention described, the screw 5 is an M5 × 1.0 screw.
The operation process of the invention is as follows:
the invention is arranged on an engine case (used for T2 measurement) mounting seat, then the engine is started to run and test, after the necessary function check is finished, when the vehicle is in a slow running state, an operator uses a sleeve to remove a plug cover arranged on the engine, a T2 thermocouple is arranged on the engine case, screws are screwed on, after the recording performance of the engine is finished, the T2 thermocouple is detached in the slow running state, the plug cover is arranged on the engine case (used for T2 measurement) mounting seat, and the subsequent engine test content is finished. The blanking cover is at the dismouting in-process, and nut 6 is spacing between spacing dish 3 of screw and blanking cover plate 4 to prevent that screw 5 from droing the mistake and going into inside the engine.
The invention has obvious implementation effect in the test run of the engine bench, can reduce the starting times of the engine, reduce the fuel consumption of the test run of the engine and save the test run cost which can reach more than 100 ten thousand yuan per year.
The above embodiments are merely illustrative of the technical ideas and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and implement the present invention, and not to limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered within the protection scope of the present invention.
Claims (4)
1. A special blanking cover for the measurement of an aircraft engine T2, comprising: the device comprises an operating rod (1), a handle (2), a screw limiting disc (3), a blocking cover plate (4), two screws (5) and two nuts (6); handle (2) are located action bars (1) upper end, the spacing dish of screw (3) and stifled apron (4) are arranged from top to bottom, correspond threaded connection in action bars (1) lower part, all correspond on spacing dish of screw (3) and the stifled apron (4) and be equipped with two through-holes, two screw (5) correspond the through-hole that passes on spacing dish of screw (3) and the stifled apron (4) and cooperate and have nut (6), nut (6) are spacing between spacing dish of screw (3) and stifled apron (4) to prevent that screw (5) from droing.
2. The special blanking cover for the measurement of the aeroengine T2 according to claim 1, wherein the screw limiting disc (3) is consistent with the blanking cover plate (4) in shape and size.
3. A special closure for the measurement of aeroengines T2, according to claim 1, wherein the handle (2) is ring-shaped.
4. A special closure for the measurement of aeroengines T2, according to claim 1, wherein the screws (5) are M5 x 1.0 screws.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011037399.2A CN112362350A (en) | 2020-09-28 | 2020-09-28 | Special blanking cover for T2 measurement of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011037399.2A CN112362350A (en) | 2020-09-28 | 2020-09-28 | Special blanking cover for T2 measurement of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112362350A true CN112362350A (en) | 2021-02-12 |
Family
ID=74508065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011037399.2A Pending CN112362350A (en) | 2020-09-28 | 2020-09-28 | Special blanking cover for T2 measurement of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112362350A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201604115U (en) * | 2010-05-07 | 2010-10-13 | 北京飞机维修工程有限公司 | Puller for disassembling blocking cap of water tank of airplane |
| DE102010051825A1 (en) * | 2010-11-18 | 2012-07-12 | Yakiv Cherkasky | Internal combustion engine mounted on vehicle e.g. car, has supplementary portion which is in form of nut that is secured at connecting rod through screw |
| CN103128531A (en) * | 2013-03-15 | 2013-06-05 | 天津正展昌电子科技有限公司 | Dismounting device for plug cover |
| CN204450417U (en) * | 2014-11-21 | 2015-07-08 | 中国飞行试验研究院 | High and low pressure turbine checks blanking cover dismantling device |
| CN207423531U (en) * | 2017-11-20 | 2018-05-29 | 中国航发沈阳发动机研究所 | Aeroengine test instrument blanking cover |
| CN208391932U (en) * | 2018-06-05 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of test instrumentation disassembling blocking cap structure |
| CN208935124U (en) * | 2018-09-25 | 2019-06-04 | 瑞安市乐舟紧固件有限公司 | Bolt structure is not deviate from a kind of floating |
| CN210769061U (en) * | 2019-11-08 | 2020-06-16 | 天津斯派恩航空防护装备有限公司 | Inner and outer duct blanking cover assembly of aircraft engine |
-
2020
- 2020-09-28 CN CN202011037399.2A patent/CN112362350A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201604115U (en) * | 2010-05-07 | 2010-10-13 | 北京飞机维修工程有限公司 | Puller for disassembling blocking cap of water tank of airplane |
| DE102010051825A1 (en) * | 2010-11-18 | 2012-07-12 | Yakiv Cherkasky | Internal combustion engine mounted on vehicle e.g. car, has supplementary portion which is in form of nut that is secured at connecting rod through screw |
| CN103128531A (en) * | 2013-03-15 | 2013-06-05 | 天津正展昌电子科技有限公司 | Dismounting device for plug cover |
| CN204450417U (en) * | 2014-11-21 | 2015-07-08 | 中国飞行试验研究院 | High and low pressure turbine checks blanking cover dismantling device |
| CN207423531U (en) * | 2017-11-20 | 2018-05-29 | 中国航发沈阳发动机研究所 | Aeroengine test instrument blanking cover |
| CN208391932U (en) * | 2018-06-05 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of test instrumentation disassembling blocking cap structure |
| CN208935124U (en) * | 2018-09-25 | 2019-06-04 | 瑞安市乐舟紧固件有限公司 | Bolt structure is not deviate from a kind of floating |
| CN210769061U (en) * | 2019-11-08 | 2020-06-16 | 天津斯派恩航空防护装备有限公司 | Inner and outer duct blanking cover assembly of aircraft engine |
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| 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: 20210212 |
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| RJ01 | Rejection of invention patent application after publication |