CN109405987B - Method for manufacturing high-temperature thermocouple assembly and high-temperature thermocouple - Google Patents
Method for manufacturing high-temperature thermocouple assembly and high-temperature thermocouple Download PDFInfo
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- CN109405987B CN109405987B CN201811538075.XA CN201811538075A CN109405987B CN 109405987 B CN109405987 B CN 109405987B CN 201811538075 A CN201811538075 A CN 201811538075A CN 109405987 B CN109405987 B CN 109405987B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
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- 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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- Measuring Temperature Or Quantity Of Heat (AREA)
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Abstract
The application discloses a method for manufacturing a high-temperature thermocouple assembly and the high-temperature thermocouple assembly. The method for manufacturing the high-temperature thermocouple assembly comprises the following steps of: step 1: the ceramic fiber-coated B-type thermocouple wire is sleeved in the protective sleeve; step 2: the tail end of the protective sleeve is sleeved again by using the sleeve, and the shrink-sealing is carried out by using the heat-shrinkable tube; and step 3: sleeving the thermocouple wire at the measuring point position at the end part of the B-type thermocouple wire wrapped by the ceramic fiber in a lead hole of the corundum ceramic tube; and 4, step 4: the thermocouple wire, the corundum porcelain tube and the protective sleeve are sleeved in the inner stepped hole of the thermocouple wire mounting seat together to form the high-temperature thermocouple assembly.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to a method for manufacturing a high-temperature thermocouple assembly and a high-temperature thermocouple.
Background
At present, a high-temperature thermocouple with an air cooling or water cooling structure is mainly used for testing the temperature of high-temperature fuel gas. Because the thermocouple bearing component needs to be cooled, the whole thermocouple structure is complex, and a test bed is additionally provided with a cooling pipeline of a sensitive part and a pipeline control system.
The whole engine is compact in structure, the cooling probe is large in structure due to the cooling flow channel, and the test modification is difficult to realize, so that the cooling probe is commonly used for part tests. Because the high-temperature thermocouples with the cooling structures mostly adopt an external plug-in mounting mode, a test flow channel can be blocked, and the arrangement quantity of the cooling type high-temperature thermocouples with the same test section is limited in order not to influence the normal performance of an engine.
The cooling flow path and boundary conditions of the cooling type probe are complex, the strength of a probe bearing part is difficult to accurately evaluate, the cooling capacity is too large, the thermal conduction error of a thermocouple is easy to increase, the cooling capacity is too small, the bearing component cannot obtain an ideal cooling effect, the safety cannot be guaranteed, and the use risk of the whole machine is high. In addition, because the structure of the whole engine is limited and the rack equipment of the whole engine cannot provide a cooling medium for the high-temperature thermocouple, the high-temperature thermocouple with the cooling structure cannot be applied to the test of the whole engine.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Content of application
It is an object of the present application to provide a method of making a high temperature thermocouple assembly that overcomes or at least alleviates at least one of the above-mentioned deficiencies in the prior art.
To achieve the above objects, the present application provides a method of fabricating a high temperature thermoelement assembly, the method of fabricating the high temperature thermoelement assembly comprising the steps of:
step 1: one end of the ceramic fiber-coated B-type thermocouple wire is sleeved in the protective sleeve;
step 2: the tail end of the protective sleeve is sleeved again by using the sleeve, and the protective sleeve and the heat-shrinkable tube are shrunk and sealed together;
and step 3: removing a ceramic fiber coating layer and an outer shielding layer from the positions of the measuring points at the end parts of the B-type idol silk coated by the ceramic fibers, respectively sleeving two poles of the idol silk in lead holes of the corundum ceramic tube, and beating hot points on the two poles of the idol silk;
and 4, step 4: after hot junction points are formed on the two poles of the idol wire, the thermal junction points, the corundum porcelain tube and the protection sleeve are sleeved in the inner stepped hole of the idol wire mounting seat in a penetrating mode, the protection sleeve and the idol wire mounting seat are welded, and high-temperature glue is smeared between the two poles of the idol wire and the lead hole of the corundum porcelain tube to fix the two poles of the idol wire and the lead hole of the corundum porcelain tube, so that a high-temperature thermocouple assembly is formed.
Optionally, the lead hole size of the corundum porcelain tube is Φ 0.6.
Optionally, the protective sleeve and the thermocouple wire mounting seat are welded by laser welding.
The application also provides a high-temperature thermocouple assembly, which is manufactured by adopting the method for manufacturing the high-temperature thermocouple.
Optionally, the high temperature thermocouple assembly comprises: coating the B-type thermocouple wires with ceramic fibers; the middle part of the coupling wire mounting seat is provided with a stepped hole; the corundum porcelain tube is provided with two threading holes, the corundum porcelain tube is arranged in the stepped hole, and the threading holes are used for penetrating the ceramic fiber coated B-type idol; the protective sleeve is arranged at the joint of the coupling wire mounting seat and the ceramic fiber-coated B-type coupling wire; the sleeve is arranged in the middle of the B-type thermocouple wire coated by the ceramic fiber, and a heat-shrinkable tube is arranged on the outer side of the sleeve; one end of the ceramic fiber coated B-type thermocouple wire is connected with the thermocouple wire mounting seat; and the other end of the ceramic fiber coated B-type thermocouple wire is connected with the tail component.
The high-temperature thermocouple assembly can be used for testing high-temperature gas at the outlet of the complete combustion chamber of the gas turbine; the measuring points are directly arranged on the front edge of the guide vane of the high-pressure turbine, so that the influence on the blockage of the whole test flow channel can be ignored; this application is direct to regard as thermocouple load-carrying component with high-pressure turbine guide vane, and the lead wire is accomplished at the turbine inner chamber to high temperature couple silk, need not coolant, and experimental risk is lower.
Drawings
FIG. 1 is a schematic flow diagram of a method of making a high temperature thermocouple assembly according to the present application.
Fig. 2 is a schematic view of the installation of a high-temperature thermocouple assembly according to a first embodiment of the present application.
Fig. 3 is a schematic structural view of the high-temperature thermoelement assembly shown in fig. 2.
Fig. 4 is a schematic view illustrating a thermocouple wire mounting seat structure of the high temperature thermocouple assembly shown in fig. 3.
Reference numerals:
1-turbine high-guide vane, 2-thermocouple assembly, 3-corundum porcelain tube, 4-thermocouple wire mounting seat, 5-protective sleeve, 6-sleeve, 7-heat-shrinkable tube, 8-ceramic fiber coated B-type thermocouple wire and 9-thermocouple tail assembly.
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 the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner and are not to be considered limiting of the scope of the present application.
FIG. 1 is a schematic flow diagram of a method of making a high temperature thermocouple assembly according to the present application.
Fig. 2 is a schematic view of the installation of a high-temperature thermocouple assembly according to a first embodiment of the present application.
Fig. 3 is a schematic structural view of the high-temperature thermoelement assembly shown in fig. 2.
Fig. 4 is a schematic view illustrating a thermocouple wire mounting seat structure of the high temperature thermocouple assembly shown in fig. 3.
The method of fabricating the high temperature thermocouple assembly shown in fig. 1 includes the steps of:
step 1: one end of the ceramic fiber coated B-type thermocouple wire 8 is sleeved in the protective sleeve 5;
step 2: the end of the protective sleeve 5 is sleeved again by a sleeve 6, and the protective sleeve and the sleeve are shrunk and sealed together by a heat shrinkable tube 7;
and step 3: removing a ceramic fiber coating layer and an outer shielding layer from the measuring point position of the end part of the B-type idol wire 8 coated by the ceramic fiber, respectively sleeving two poles of the idol wire in lead holes of the corundum ceramic tube 3 in a penetrating way, and beating hot points on the two poles of the idol wire;
and 4, step 4: after hot junction points are punched on the two poles of the idol wire, the thermal junction points, the corundum porcelain tube 3 and the protective sleeve 5 are sleeved in the inner stepped hole of the idol wire mounting seat 4 together in a penetrating mode, the protective sleeve 5 and the idol wire mounting seat 4 are welded, and high-temperature glue is smeared between the two poles of the idol wire and the lead hole of the corundum porcelain tube 3 for fixing, so that the high-temperature thermocouple assembly 2 is formed.
In the present embodiment, the lead hole size of the corundum porcelain tube 3 is Φ 0.6.
In this embodiment, the protection sleeve 5 and the wire coupling mounting seat 4 are welded by laser welding.
The application also provides a high-temperature thermocouple assembly which is manufactured by the method for manufacturing the high-temperature thermocouple.
In this embodiment, the high temperature thermocouple assembly includes:
coating the B-type thermocouple wires with ceramic fibers;
the middle part of the coupling wire mounting seat is provided with a stepped hole;
the corundum porcelain tube is provided with two threading holes, the corundum porcelain tube is arranged in the stepped hole, and the threading holes are used for penetrating the ceramic fiber coated B-type idol;
the protective sleeve is arranged at the joint of the coupling wire mounting seat and the ceramic fiber-coated B-type coupling wire;
the sleeve is arranged in the middle of the B-type thermocouple wire coated by the ceramic fiber, and a heat-shrinkable tube is arranged on the outer side of the sleeve;
one end of the ceramic fiber coated B-type thermocouple wire is connected with the thermocouple wire mounting seat;
and the other end of the ceramic fiber coated B-type thermocouple wire is connected with the tail component.
The high-temperature thermocouple can be used for testing high-temperature gas at the outlet of the combustion chamber of the whole gas turbine; the measuring points are directly arranged on the front edge of the guide vane of the high-pressure turbine, so that the influence on the blockage of the whole test flow channel can be ignored; this application is direct to regard as thermocouple load-carrying component with high-pressure turbine guide vane, and the lead wire is accomplished at the turbine inner chamber to high temperature couple silk, need not coolant, and experimental risk is lower.
The high-temperature thermocouple for measuring the temperature of the outlet of the whole engine combustion chamber comprises a turbine high-guide vane 1 and a high-temperature thermocouple assembly 2, as shown in FIG. 1. The high-temperature thermocouple assembly 2 comprises a corundum porcelain tube 3, a thermocouple wire mounting seat 4, a protective sleeve 5, a sleeve 6, a heat-shrinkable tube 7, a ceramic fiber coated B-type thermocouple wire 8 and a thermocouple tail assembly 9, and is shown in figure 3. One end of the ceramic fiber coated B-type thermocouple wire 8 is sleeved in the protective sleeve 5, so that the thermocouple part in the cooling gas environment is ensured to be sleeved in the protective sleeve 5. The end of the protective sleeve 5 is reeved with a sleeve 6 and shrink-sealed with a heat shrink tube 7. The ceramic fiber coating layer and the outer shielding layer are stripped at the measuring point position of the end part of the B-type idol wire 8, the two poles of the idol wire are respectively sleeved in phi 0.6 lead holes of the corundum porcelain tube 3 in a penetrating way, and the two poles of the idol wire are heated. After hot junction points are punched on the two poles of the idol wire, the thermal junction points, the corundum porcelain tube 3 and the protection sleeve 5 are sleeved in the inner stepped hole of the idol wire mounting seat 4 together in a penetrating mode, the protection sleeve 5 and the idol wire mounting seat 4 (the position C in the figure 2) are welded through laser welding, high-temperature glue is properly coated between the two poles of the idol wire and the lead hole (the position B in the figure 2) of the corundum porcelain tube 3 to be fixed, and therefore the high-temperature thermocouple assembly 2 is machined.
The front edge of the high-pressure turbine guide vane 1 is pre-processed with a test mounting hole, communicated with a cooling cavity on the vane, and matched with the overall dimension of the coupling wire mounting seat 4 in size. And (2) sequentially installing the machined thermocouple wire mounting seat 4 with the thermocouple wire hot junction on the high-temperature thermocouple assembly 2 into a pre-machined test mounting hole at the front edge of the high-pressure turbine guide vane 1 from a cooling cavity of the high-pressure turbine guide vane, performing rotary laser welding on the thermocouple wire mounting seat 4 and the pressure turbine guide vane 1 (A position in the figure 1), polishing a welding port after welding is completed, and spraying a high-temperature coating. And (4) finishing the processing of the thermocouple tail component 9 after the test lead is led out of the engine culvert casing.
According to the high-temperature thermocouple, the high-pressure turbine guide vane is directly used as a force bearing component of the sensing part, a test lead is completed by utilizing the cooling cavity in the high-pressure turbine guide vane, and the thermocouple does not need to be cooled independently;
according to the high-temperature thermocouple, the B-type thermocouple wire coated with the ceramic fiber is sleeved inside the protective sleeve in a penetrating manner, so that the turbine cooling gas is prevented from permeating to influence the test result;
the high-temperature thermocouple realizes the test of the outlet temperature of the combustion chamber by directly welding the thermocouple wire mounting seat on the front edge of the guide vane of the high-pressure turbine, and the influence on the blockage of the engine runner can be ignored.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present application, and are not limited thereto. Although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (3)
1. A method of fabricating a high temperature thermocouple assembly, comprising the steps of:
step 1: one end of the ceramic fiber-coated B-type thermocouple wire (8) is sleeved in the protective sleeve (5);
step 2: the tail end of the protective sleeve (5) is sleeved again by a sleeve (6) and is shrunk and sealed together by a heat shrinkable tube (7);
and step 3: removing a ceramic fiber coating layer and an outer shielding layer from the position of a measuring point at the end part of a B-type idol wire (8) coated by a ceramic fiber, respectively sleeving two poles of the idol wire in lead holes of a corundum ceramic tube (3) in a penetrating way, and beating hot points on the two poles of the idol wire;
and 4, step 4: after hot junction points are punched on the two poles of the idol wire, the two poles of the idol wire together with the corundum porcelain tube (3) and the protective sleeve (5) are sleeved in the inner stepped hole of the idol wire mounting seat (4) in a penetrating way, the protective sleeve (5) and the idol wire mounting seat (4) are welded, and high-temperature glue is smeared between the two poles of the idol wire and the lead hole of the corundum porcelain tube (3) for fixing, so that a high-temperature thermocouple assembly (2) is formed;
the high-temperature thermocouple manufactured by the method for manufacturing the high-temperature thermocouple assembly comprises the following steps:
coating the B-type thermocouple wires with ceramic fibers;
the middle part of the coupling wire mounting seat is provided with a stepped hole;
the corundum porcelain tube is provided with two threading holes, the corundum porcelain tube is arranged in the stepped hole, and the threading holes are used for penetrating the ceramic fiber coated B-type idol;
the protective sleeve is arranged at the joint of the coupling wire mounting seat and the ceramic fiber-coated B-type coupling wire;
the sleeve is arranged in the middle of the B-type thermocouple wire coated by the ceramic fiber, and a heat-shrinkable tube is arranged on the outer side of the sleeve;
one end of the ceramic fiber coated B-type thermocouple wire is connected with the thermocouple wire mounting seat;
the other end of the ceramic fiber coated B-type thermocouple wire is connected with the tail component;
the method comprises the steps that a test mounting hole is machined in advance in the front edge of the high-pressure turbine guide vane and communicated with a cooling cavity on the vane, the size of the test mounting hole is matched with the overall size of a thermocouple wire mounting seat, the thermocouple wire mounting seat with a thermocouple wire hot junction on a machined high-temperature thermocouple assembly is sequentially installed in the test mounting hole machined in advance in the front edge of the high-pressure turbine guide vane from the cooling cavity of the high-pressure turbine guide vane, the thermocouple wire mounting seat and the high-pressure turbine guide vane are subjected to rotary laser welding, after welding is completed, a welding port is polished, a high-temperature coating is sprayed, and after a test lead is led out of an engine external culvert casing, the machining of a thermocouple tail assembly is completed;
the testing lead wire is completed by utilizing the cooling cavity in the guide vane of the high-pressure turbine, and the thermocouple does not need to be cooled separately.
2. A method of high temperature thermocouple assembly according to claim 1 wherein the leadthrough size of the corundum porcelain tube (3) is Φ 0.6.
3. A method of high temperature thermocouple assembly according to claim 1, characterized in that the welding between the protective sleeve (5) and the thermocouple wire mount (4) is performed by laser welding.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811538075.XA CN109405987B (en) | 2018-12-16 | 2018-12-16 | Method for manufacturing high-temperature thermocouple assembly and high-temperature thermocouple |
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| CN201811538075.XA CN109405987B (en) | 2018-12-16 | 2018-12-16 | Method for manufacturing high-temperature thermocouple assembly and high-temperature thermocouple |
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| CN109405987B true CN109405987B (en) | 2021-08-17 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1480109A (en) * | 1975-07-24 | 1977-07-20 | Mectron Ltd | Temperature reference apparatus |
| CN104483028A (en) * | 2014-11-05 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine high pressure turbine blade surface temperature measuring device |
| CN106932112A (en) * | 2017-02-08 | 2017-07-07 | 中国航发沈阳发动机研究所 | One kind is without cooling down high-temperature thermocouple preparation method and without cooling down high-temperature thermocouple |
| CN207556699U (en) * | 2017-12-11 | 2018-06-29 | 中国航发沈阳发动机研究所 | A kind of temperature test probe |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768441A (en) * | 2016-12-21 | 2017-05-31 | 中国燃气涡轮研究院 | A kind of Turbine Blade Temperature Field measuring method based on plasma spraying |
| CN108193163A (en) * | 2017-12-28 | 2018-06-22 | 中国航发四川燃气涡轮研究院 | A kind of high-temperature fusion thermocouple sensor manufacturing method based on flame spray powder coating |
-
2018
- 2018-12-16 CN CN201811538075.XA patent/CN109405987B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1480109A (en) * | 1975-07-24 | 1977-07-20 | Mectron Ltd | Temperature reference apparatus |
| CN104483028A (en) * | 2014-11-05 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Engine high pressure turbine blade surface temperature measuring device |
| CN106932112A (en) * | 2017-02-08 | 2017-07-07 | 中国航发沈阳发动机研究所 | One kind is without cooling down high-temperature thermocouple preparation method and without cooling down high-temperature thermocouple |
| CN207556699U (en) * | 2017-12-11 | 2018-06-29 | 中国航发沈阳发动机研究所 | A kind of temperature test probe |
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