CN205719306U - A kind of 5 stagnation temperature probes of aero-engine - Google Patents
A kind of 5 stagnation temperature probes of aero-engine Download PDFInfo
- Publication number
- CN205719306U CN205719306U CN201620319917.2U CN201620319917U CN205719306U CN 205719306 U CN205719306 U CN 205719306U CN 201620319917 U CN201620319917 U CN 201620319917U CN 205719306 U CN205719306 U CN 205719306U
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- bearing
- transfer tube
- pole
- glass fiber
- mounting seat
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Abstract
A kind of 5 stagnation temperature probes of aero-engine, it is characterized in that, including bearing, stifled bar, mounting seat, pole, transfer tube and glass fiber sleeve pipe, stifled bar is arranged on bearing back, bearing is fixed in mounting seat, mounting seat connects pole, pole connects transfer tube, transfer tube connects glass fiber sleeve pipe, bearing front end is provided with 5 diplopore porcelain tubes, it is provided with thermocouple wire in diplopore porcelain tube, thermocouple wire sequentially passes through bearing, mounting seat, pole, transfer tube, glass fiber sleeve pipe, and reach outside the afterbody of glass fiber sleeve pipe, single hole porcelain tube also it is cased with on thermocouple wire, bearing, mounting seat, pole, Hot Cement all it is filled with in transfer tube, transfer tube is filled with high-temperature seal adhesive with the junction of glass fiber sleeve pipe.This structure realizes 5 temperature sensings, and certainty of measurement is high, and thermo wires protects through porcelain tube set, and all fills Hot Cement at bearing and transfer tube, and probe structure is stable, and heat-resisting ability is strong.
Description
Technical field
This utility model relates to electromotor by sense technology, particularly relates to a kind of 5 stagnation temperature probes of aero-engine.
Background technology
Aero-engine belongs to the complicated actuating unit of high load capacity, hot operation, be in the structure within nucleus of high pressure machine and relevant device bear always high temperature, high pressure, run up, the effect such as air-flow aerodynamic force impact.Existing aero-engine fault rate is concentrated mainly in the work process being in high-temp and high-strength, therefore, is the Key experiments of reliability to aero-engine thermometric.And existing probe, test error is big, probe steady is poor, structure is not reasonable, needs to be improved.
Utility model content
This utility model provides a kind of 5 stagnation temperature probes of aero-engine, and not enough to solve above-mentioned prior art, innovation structure designs, realizing 5 temperature sensings, certainty of measurement is high, and thermo wires protects through porcelain tube set, and all fill Hot Cement at bearing and transfer tube, probe structure is stable, and heat-resisting ability is strong.
The technical solution adopted in the utility model is:
A kind of 5 stagnation temperature probes of aero-engine, it is characterized in that, including bearing, stifled bar, mounting seat, pole, transfer tube and glass fiber sleeve pipe, stifled bar is arranged on bearing back, bearing is fixed in mounting seat, mounting seat connects pole, pole connects transfer tube, transfer tube connects glass fiber sleeve pipe, bearing front end is provided with 5 diplopore porcelain tubes, it is provided with thermocouple wire in diplopore porcelain tube, thermocouple wire sequentially passes through bearing, mounting seat, pole, transfer tube, glass fiber sleeve pipe, and reach outside the afterbody of glass fiber sleeve pipe, single hole porcelain tube also it is cased with on thermocouple wire, bearing, mounting seat, pole, Hot Cement all it is filled with in transfer tube, transfer tube is filled with high-temperature seal adhesive with the junction of glass fiber sleeve pipe.
Further, described thermocouple wire is K-type nickel chromium triangle-chrome-silicon thermocouple wire, a diameter of 0.5mm, and precision is 1 grade.
The beneficial effects of the utility model are:
1, being provided with 5 diplopore porcelain tubes on bearing, and use the K-type nickel chromium triangle-chrome-silicon thermocouple wire being cased with single hole porcelain tube, it is achieved 5 temperature sensings, improve certainty of measurement and measure stability, the suitability is higher；
2, bearing, stifled bar, mounting seat, pole, transfer tube and the combination of glass fiber sleeve pipe, Stability Analysis of Structures are used, it is easy to accomplish, Hot Cement and the filling of high-temperature seal adhesive, advantageously in Stability Analysis of Structures, heat-resisting ability is strong.
Accompanying drawing explanation
Fig. 1 is internal structure schematic diagram of the present utility model.
Fig. 2 is overall structure schematic diagram one of the present utility model.
Fig. 3 is overall structure schematic diagram two of the present utility model.
Detailed description of the invention
nullAs shown in accompanying drawing 1 ~ 3，A kind of 5 stagnation temperature probes of aero-engine，Including bearing 1、Stifled bar 4、Mounting seat 5、Pole 6、Transfer tube 7 and glass fiber sleeve pipe 8，Stifled bar 4 is arranged on bearing 1 back，Bearing 1 is fixed in mounting seat 5，Mounting seat 5 connects pole 6，Pole 6 connects transfer tube 7，Transfer tube 7 connects glass fiber sleeve pipe 8，Bearing 1 front end is provided with 5 diplopore porcelain tubes 2，Thermocouple wire 10 it is provided with in diplopore porcelain tube 2，Thermocouple wire 10 sequentially passes through bearing 1、Mounting seat 5、Pole 6、Transfer tube 7、Glass fiber sleeve pipe 8，And reach outside the afterbody 9 of glass fiber sleeve pipe 8，Single hole porcelain tube 3 also it is cased with on thermocouple wire 10，Bearing 1、Mounting seat 5、Pole 6、Hot Cement 11 all it is filled with in transfer tube 7，Transfer tube 7 is filled with high-temperature seal adhesive 12 with the junction of glass fiber sleeve pipe 8.Concrete, described thermocouple wire 10 is K-type nickel chromium triangle-chrome-silicon thermocouple wire, a diameter of 0.5mm, and precision is 1 grade.
Signal parameter is acquired by the K-type nickel chromium triangle-chrome-silicon thermocouple wire in 5 diplopore porcelain tubes 2, gathers backward rear transmission, after afterbody 9, is connected to subsequent detection equipment.This utility model is provided with 5 diplopore porcelain tubes 2 on bearing 1, and uses the K-type nickel chromium triangle-chrome-silicon thermocouple wire being cased with single hole porcelain tube 3, it is achieved 5 temperature sensings, improves certainty of measurement and measures stability, and the suitability is higher；Use bearing 1, stifled bar 4, mounting seat 5, pole 6, transfer tube 7 and the combination of glass fiber sleeve pipe 8, Stability Analysis of Structures, it is easy to accomplish；Hot Cement 11 and the filling of high-temperature seal adhesive 12, advantageously in Stability Analysis of Structures, heat-resisting ability is strong.
Claims (3)
- null1. 5 stagnation temperature probes of an aero-engine，It is characterized in that，Including bearing (1)、Stifled bar (4)、Mounting seat (5)、Pole (6)、Transfer tube (7) and glass fiber sleeve pipe (8)，Stifled bar (4) is arranged on bearing (1) back，Bearing (1) is fixed in mounting seat (5)，Mounting seat (5) connects pole (6)，Pole (6) connects transfer tube (7)，Transfer tube (7) connects glass fiber sleeve pipe (8)，Bearing (1) front end is provided with 5 diplopore porcelain tubes (2)，Thermocouple wire (10) it is provided with in diplopore porcelain tube (2)，Thermocouple wire (10) sequentially passes through bearing (1)、Mounting seat (5)、Pole (6)、Transfer tube (7)、Glass fiber sleeve pipe (8)，And reach the afterbody (9) of glass fiber sleeve pipe (8) outward，Single hole porcelain tube (3) also it is cased with on thermocouple wire (10)，Bearing (1)、Mounting seat (5)、Pole (6)、Hot Cement (11) all it is filled with in transfer tube (7)，Transfer tube (7) is filled with high-temperature seal adhesive (12) with the junction of glass fiber sleeve pipe (8).
- 5 stagnation temperature probes of aero-engine the most according to claim 1, it is characterised in that described thermocouple wire (10) is K-type nickel chromium triangle-chrome-silicon thermocouple wire.
- 5 stagnation temperature probes of aero-engine the most according to claim 1, it is characterised in that a diameter of 0.5mm of described thermocouple wire (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620319917.2U CN205719306U (en) | 2016-04-18 | 2016-04-18 | A kind of 5 stagnation temperature probes of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620319917.2U CN205719306U (en) | 2016-04-18 | 2016-04-18 | A kind of 5 stagnation temperature probes of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205719306U true CN205719306U (en) | 2016-11-23 |
Family
ID=57307816
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620319917.2U Expired - Fee Related CN205719306U (en) | 2016-04-18 | 2016-04-18 | A kind of 5 stagnation temperature probes of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205719306U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109341883A (en) * | 2018-10-25 | 2019-02-15 | 浙江大学 | A kind of total temperature measurement device in aeroengine combustor buring room |
-
2016
- 2016-04-18 CN CN201620319917.2U patent/CN205719306U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109341883A (en) * | 2018-10-25 | 2019-02-15 | 浙江大学 | A kind of total temperature measurement device in aeroengine combustor buring room |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20200418 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |