CN102661972B - measurement method of heat insulating property of gas turbine heat shield - Google Patents
measurement method of heat insulating property of gas turbine heat shield Download PDFInfo
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- CN102661972B CN102661972B CN201210151139.7A CN201210151139A CN102661972B CN 102661972 B CN102661972 B CN 102661972B CN 201210151139 A CN201210151139 A CN 201210151139A CN 102661972 B CN102661972 B CN 102661972B
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Abstract
The invention provides a gas turbine heat shield. A heat insulating layer structure is adopted by the gas turbine heat shield, and the gas turbine heat shield sequentially comprises a stainless steel plate, an infrared reflection plate, high silicon aluminum cloth, heat insulating ceramic cotton, heat insulating zirconium aluminum cloth and a perforated plate from outside to inside, wherein the thickness of the stainless steel plate is 2mm, the thickness of the infrared reflection plate is 1mm, the thickness of the high silicon aluminum cloth is 0.7mm, the thickness of the heat insulating ceramic cotton is 100mm, the thickness of the heat insulating zirconium aluminum cloth is 0.8mm, and the thickness of the perforated plate is 1.2mm. A heat-insulating property measurement method for the gas turbine heat shield is characterized in that on the basis of a single-layer flat wall stable heat conduction principle, a heat insulating material and the thickness of a heat insulating layer thereof, which can achieve an ideal heat insulating effect under various conditions, are tested through changing the material quality and the thickness of the heat insulating material and changing an interior temperature field of the heat shield. The gas turbine heat shield has a good heat insulating effect and can be used for guaranteeing a gas turbine to stably run, and the reliability of the gas turbine heat shield is sufficiently verified through the measurement method of the heat insulating property.
Description
Technical field
The invention relates to the assay method of a kind of gas turbine heat shield and heat-proof quality thereof, and gas turbine heat shield is used for carrying out heat insulation to gas turbine, and the assay method of its heat-proof quality is used for verifying its effect of heat insulation.
Background technology
In recent years, gas turbine gets more and more in the application of every field, but due to the position, firing chamber of gas turbine and the heat radiation of power turbine position more concentrated, cause this position space temperature too high.Temperature too high for a long time can affect the normal work of gas turbine, even damages gas turbine time serious, so just causes very large economic loss.
Traditional, the coefficient of heat conductivity of insulation material adopts the thermal conductivity measuring apparatus of specialty to carry out Accurate Measurement, but this assay method compares scientific research, design, production unit etc. that the condition of being applicable to is engaged in insulation material professional work preferably.
Summary of the invention
The object of the invention is to provide the assay method of a kind of gas turbine heat shield and heat-proof quality thereof, gas turbine heat shield has good effect of heat insulation, gas turbine even running can be made, and fully verified by the reliability of assay method to gas turbine heat shield of heat-proof quality.
The technical scheme of the invention: gas turbine heat shield adopts heat insulation layer structure, gas turbine heat shield is from being followed successively by corrosion resistant plate, infrared reflection plate, high sial cloth, heat preserving ceramic cotton, insulation zirconium aluminium cloth and perforated plate outward to heat shield.
The material of corrosion resistant plate is 304 steel plates, and the material of infrared reflection plate is aluminium, and the material of perforated plate is steel.
The thickness of described corrosion resistant plate is 1-3mm, and the thickness of infrared reflection plate is 0.5-1.5mm, and the thickness of high sial cloth is 0.7mm, and the thickness of heat preserving ceramic cotton is 50-100mm, and the thickness of insulation zirconium aluminium cloth is 0.8mm, and the thickness of perforated plate is 1-2mm.
The thickness of described corrosion resistant plate is 2mm, and the thickness of infrared reflection plate is 1mm, and the thickness of high sial cloth is 0.7mm, and the thickness of heat preserving ceramic cotton is 100mm, and the thickness of insulation zirconium aluminium cloth is 0.8mm, and the thickness of perforated plate is 1.2mm.
The assay method of the heat-proof quality of gas turbine heat shield, concrete grammar is as follows:
1) make insulation cylindrical shell and insulation closure plate, insulation cylindrical shell and insulation closure plate form airtight chamber;
2) on insulation cylindrical shell, install two pairs of galvanic couple sockets, the often pair of galvanic couple socket is placed in the inside and outside both sides of insulation cylindrical shell respectively and position is corresponding, and galvanic couple socket is placed with galvanic couple, and a pair galvanic couple is connected with a digital display type multi-point thermo detector by wire;
3) be placed with electrothermal furnace in airtight chamber, electrothermal furnace is connected with the heating arrangement inside and outside airtight chamber by wire;
4) this assay method is based on individual layer planomural steady heat conduction principle, the heat Q:Q=of individual layer planomural heat-insulation layer conduction
,
Heat-insulation layer outer wall heat dissipation capacity Q
s: Q
s=
,
Due to steady heat conduction, Q=Q
s, namely
=
,
Can obtain:
/ (m.k),
Wherein, Q-heat-insulation layer heat conduction, W;
Q
s-heat-insulation layer outer wall heat dissipation capacity, W;
λ-insulation material coefficient of heat conductivity ,/(m.k);
δ-insulation layer thickness, m;
F-perpendicular to the surface area of direction of heat flow, m
2;
F
wb-heat-insulation layer outer wall area, m
2;
T
wa-heat-insulation layer inner wall temperature, DEG C;
T
wb-heat-insulation layer outside wall temperature, DEG C;
T
0-environment temperature, DEG C;
the integrated heat transfer coefficient that-heat-insulation layer outer wall outwardly conducts heat, W/(m
2.k);
5) by changing the material of insulation material and changing the thickness of insulation material, and change heat shield internal temperature field, test the insulation material and insulation layer thickness thereof that can reach desirable heat insulation effect under various conditions;
6) the insulation data respectively under the above various condition of record also contrast, obtain heat insulation effect preferably and can satisfied temperature requirement insulation material and at different temperatures best insulation thickness after the match.
The beneficial effect of the invention: corrosion resistant plate plays the effect supporting whole heat shield, infrared reflection plate will go back to heat shield inside to extraradial heat, reduce to extraradial heat, high sial cloth plays insulation effect to heat preserving ceramic cotton, heat preserving ceramic cotton has good effect of heat insulation, insulation zirconium aluminium cloth plays the cotton overall outer supporting role of heat preserving ceramic, and prevent the coking of heat preserving ceramic cotton, perforated plate is used for transferring heat; In heat shield, the thickness of corrosion resistant plate is 2mm, the thickness of infrared reflection plate is 1mm, the thickness of high sial cloth is 0.7mm, and the thickness of heat preserving ceramic cotton is 100mm, and the thickness of insulation zirconium aluminium cloth is 0.8mm, the thickness of perforated plate is 1.2mm, make heat shield have good effect of heat insulation, and the overall operation of gas turbine can be ensured, extend the serviceable life of gas turbine; The assay method of the heat-proof quality adopted based on individual layer planomural steady heat conduction principle, fully and demonstrate the effect of heat insulation of heat shield accurately.
Accompanying drawing explanation
Fig. 1 is the structural representation of gas turbine heat shield.
Fig. 2 is the determinator schematic diagram of gas turbine heat shield heat-proof quality.
Fig. 3 is the side view of Fig. 2.
Fig. 4 is the structural representation of heat-insulation layer.
Embodiment
As shown in Figure 1 and Figure 4, gas turbine heat shield, gas turbine heat shield is from being followed successively by corrosion resistant plate (6), infrared reflection plate (7), high sial cloth (8), heat preserving ceramic cotton (9), insulation zirconium aluminium cloth (10) and perforated plate (11) outward to heat shield.
The material of corrosion resistant plate (6) is 304 steel plates, and the material of infrared reflection plate (7) is aluminium, and the material of perforated plate (11) is steel.
The thickness of described corrosion resistant plate (6) is 1-3mm, the thickness of infrared reflection plate (7) is 0.5-1.5mm, the thickness of high sial cloth (8) is 0.7mm, the thickness of heat preserving ceramic cotton (9) is 50-100mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, and the thickness of perforated plate (11) is 1-2mm.
The thickness of described corrosion resistant plate (6) is 2mm, the thickness of infrared reflection plate (7) is 1mm, and the thickness of high sial cloth (8) is 0.7mm, and the thickness of heat preserving ceramic cotton (9) is 100mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, and the thickness of perforated plate (11) is 1.2mm.
As shown in Figures 2 and 3, the assay method of gas turbine heat shield heat-proof quality, concrete grammar is as follows:
1) make insulation cylindrical shell (1) and insulation closure plate (2), insulation cylindrical shell (1) and insulation closure plate (2) form airtight chamber;
2) the upper installation two pairs of galvanic couple sockets (3) of insulation cylindrical shell (1), the often pair of galvanic couple socket (3) is placed in the inside and outside both sides of insulation cylindrical shell (1) respectively and position is corresponding, (3) are placed with galvanic couple with galvanic couple socket, and a pair galvanic couple is connected with a digital display type multi-point thermo detector (4) by wire;
3) be placed with electrothermal furnace in airtight chamber, electrothermal furnace is connected with the heating arrangement (5) inside and outside airtight chamber by wire;
4) this assay method is based on individual layer planomural steady heat conduction principle, the heat Q:Q=of individual layer planomural heat-insulation layer conduction
,
Heat-insulation layer outer wall heat dissipation capacity Q
s: Q
s=
,
Due to steady heat conduction, Q=Q
s, namely
=
,
Can obtain:
/ (m.k), in table 1;
Wherein, Q-heat-insulation layer heat conduction, W;
Q
s-heat-insulation layer outer wall heat dissipation capacity, W;
λ-insulation material coefficient of heat conductivity ,/(m.k);
δ-insulation layer thickness, m;
F-perpendicular to the surface area of direction of heat flow, m
2;
F
wb-heat-insulation layer outer wall area, m
2;
T
wa-heat-insulation layer inner wall temperature, DEG C;
T
wb-heat-insulation layer outside wall temperature, DEG C;
T
0-environment temperature, DEG C;
the integrated heat transfer coefficient that-heat-insulation layer outer wall outwardly conducts heat, W/(m
2.k);
5) by changing the material of insulation material and changing the thickness of insulation material, and change heat shield internal temperature field, test the insulation material and insulation layer thickness thereof that can reach desirable heat insulation effect under various conditions;
6) the insulation data respectively under the above various condition of record also contrast, obtain heat insulation effect preferably and can satisfied temperature requirement insulation material and at different temperatures best insulation thickness after the match.
Table 1
Find in above-mentioned test, 304 corrosion resistant plates, easily producing distortion lower than welding during 2mm, can not reach the overall requirement of heat shield.Therefore, corrosion resistant plate 6(304 steel plate) thickness be chosen as 2mm.
Because the usage space of heat shield is limited, therefore, the maximum gauge of heat shield is 100mm.
embodiment one:the thickness of corrosion resistant plate (6) is 2mm, the thickness of high temperature resistant aluminium cloth is 0.7mm, the thickness of heat preserving ceramic cotton (9) is 100mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, the thickness of perforated plate (11) is 2mm, gross thickness is 105.7mm, then heat shield integral thickness is compressed to 100mm, the effect of heat insulation of heat shield and the coefficient of heat conductivity of each heat-insulation layer thereof during test heat shield internal temperature field difference 300 DEG C, 350 DEG C, 400 DEG C, 450 DEG C, 500 DEG C, 550 DEG C, 600 DEG C, see table 2.
Table 2
| Project | Unit | Data Source | Measuring point area | Insulation construction thickness | Heat source temperature | Burner hearth measuring point A temperature | Outer wall measuring point A temperature | Burner hearth measuring point B temperature | Outer wall measuring point B temperature | Environment temperature |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 300℃ | 300℃ | 48℃ | 300℃ | 47℃ | 17℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 350℃ | 350℃ | 62℃ | 350℃ | 60℃ | 16℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 400℃ | 400℃ | 79℃ | 400℃ | 77℃ | 16℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 450℃ | 450℃ | 91℃ | 450℃ | 90℃ | 18℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 500℃ | 500℃ | 101℃ | 500℃ | 98℃ | 17℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 550℃ | 550℃ | 150℃ | 550℃ | 148℃ | 19℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 600℃ | 600℃ | 198℃ | 600℃ | 195℃ | 17℃ |
As can be seen from Table 1: when experiment proceeds to 600 degrees Celsius, heat shield outside wall temperature has reached 195 DEG C, because temperature is too high, do not continue the necessity tested, therefore, terminated this time test, carried out the redesign work of stay-warm case.
embodiment two:the basis of embodiment one adds infrared reflection plate (7), the thickness of infrared reflection plate (7) is 1.5mm, then heat shield integral thickness is compressed to 100mm, the effect of heat insulation of heat shield during test heat shield internal temperature field difference 300 DEG C, 350 DEG C, 400 DEG C, 450 DEG C, 500 DEG C, 550 DEG C, 600 DEG C, 650 DEG C, 700 DEG C, 750 DEG C, 800 DEG C, 850 DEG C, see table 3.
Table 3
| Project | Unit | Data Source | Measuring point area | Insulation construction thickness | Heat source temperature | Burner hearth measuring point A temperature | Outer wall measuring point A temperature | Burner hearth measuring point B temperature | Outer wall measuring point B temperature | Environment temperature |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 300℃ | 300℃ | 25℃ | 300℃ | 24℃ | 12℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 350℃ | 350℃ | 29℃ | 350℃ | 29℃ | 12℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 400℃ | 400℃ | 31℃ | 400℃ | 30℃ | 11℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 450℃ | 450℃ | 36℃ | 450℃ | 34℃ | 11℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 500℃ | 500℃ | 42℃ | 500℃ | 40℃ | 13℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 550℃ | 550℃ | 48℃ | 550℃ | 47℃ | 13℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 600℃ | 600℃ | 53℃ | 600℃ | 51℃ | 14℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 650℃ | 650℃ | 60℃ | 647℃ | 61℃ | 14℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 700℃ | 700℃ | 66℃ | 700℃ | 65℃ | 10℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 750℃ | 750℃ | 72℃ | 750℃ | 72℃ | 11℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 800℃ | 800℃ | 78℃ | 800℃ | 77℃ | 12℃ |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 850℃ | 850℃ | 95℃ | 850℃ | 94℃ | 12℃ |
As can be seen from Table 3, although this time test findings of test is satisfactory, there are two very serious problems:
1. find that the phenomenon that coking is serious appears in the high temperature resistant aluminium cloth to heat preserving ceramic cotton plays a protective role.The effect of protection can not have been played to heat preserving ceramic cotton.As long-time running on gas turbine, grievous injury will inevitably be produced to heat preserving ceramic cotton, make stay-warm case there is no permanance, therefore change high temperature resistant aluminium cloth into high temperature resistant sial cloth;
2. stay-warm case is when being arranged on gas turbine, and after with the addition of infrared reflection plate, overall weight increases, and makes overall gas turbine overload, produces surge.As there is surge by the overall even running of gas turbine and cause serious injury serviceable life in gas turbine.And infrared reflection plate will reduce greatly lower than infrared reflection effect during 1mm.Therefore when again having carried out new design to heat shield, the thickness of infrared reflection plate is chosen as 1mm, to reach the object of gas turbine Reduction of Students' Study Load.
embodiment three:the thickness of corrosion resistant plate (6) is 2mm, the thickness of infrared reflection plate (7) is 1mm, the thickness of high sial cloth (8) is 0.7mm, the thickness of heat preserving ceramic cotton (9) is 100mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, the thickness of perforated plate (11) is 2mm, gross thickness is 105.7mm, then heat shield integral thickness is compressed to 100mm, 300 DEG C respectively, test heat shield internal temperature field, 400 DEG C, 450 DEG C, 500 DEG C, 550 DEG C, 600 DEG C, 650 DEG C, 700 DEG C, 750 DEG C, 800 DEG C, the effect of heat insulation of heat shield and rate of heat dissipation when 850 DEG C, and by stay-warm case mean coefficient of heat conductivity
/ (m.k) calculation of thermal conductivity, see table 4.
Table 4
| Project | Unit | Data Source | Measuring point area | Insulation construction thickness | Heat source temperature | Burner hearth measuring point A temperature | Outer wall measuring point A temperature | Burner hearth measuring point B temperature | Outer wall measuring point B temperature | Environment temperature | Rate of heat dissipation |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 300 ℃ | 300 ℃ | 26℃ | 300 ℃ | 23℃ | 12℃ | 95.14% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 350℃ | 350℃ | 30℃ | 350 | 29℃ | 12℃ | 94.7% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 400℃ | 400℃ | 33℃ | 400℃ | 29℃ | 11℃ | 94.34% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 450℃ | 450℃ | 37℃ | 450℃ | 33℃ | 11℃ | 94.03% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 500℃ | 500℃ | 43℃ | 500℃ | 40℃ | 13℃ | 93.84% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 550℃ | 550℃ | 50℃ | 550℃ | 48℃ | 13℃ | 93.1% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 600℃ | 600℃ | 55℃ | 600℃ | 53℃ | 14℃ | 93% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 650℃ | 650℃ | 62℃ | 647℃ | 61℃ | 14℃ | 92.34% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 700℃ | 700℃ | 66℃ | 700℃ | 65℃ | 10℃ | 91.88% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 750℃ | 750℃ | 74℃ | 750℃ | 73℃ | 11℃ | 91.34% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 800℃ | 800℃ | 82℃ | 800℃ | 81℃ | 12℃ | 91.12% |
| Heat insulation test | cm | Actual measurement | 5*10 | 10 | 850℃ | 850℃ | 98℃ | 850℃ | 97℃ | 12℃ | 89.54% |
embodiment four:the thickness of corrosion resistant plate (6) is 2mm, the thickness of infrared reflection plate (7) is 1mm, the thickness of high sial cloth (8) is 0.7mm, the thickness of heat preserving ceramic cotton (9) is 70mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, the thickness of perforated plate (11) is 2mm, gross thickness is 75.7mm, then heat shield integral thickness is compressed to 70mm, 300 DEG C respectively, test heat shield internal temperature field, 400 DEG C, 450 DEG C, 500 DEG C, 550 DEG C, 600 DEG C, 650 DEG C, 700 DEG C, 750 DEG C, 800 DEG C, the effect of heat insulation of heat shield and rate of heat dissipation thereof when 850 DEG C, and by stay-warm case mean coefficient of heat conductivity
/ (m.k) calculation of thermal conductivity, see table 5.
Table 5
| Project | Unit | Data Source | Measuring point area | Insulation construction thickness | Heat source temperature | Burner hearth measuring point A temperature | Outer wall measuring point A temperature | Burner hearth measuring point B temperature | Outer wall measuring point B temperature | Environment temperature | Rate of heat dissipation |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 300℃ | 300℃ | 37℃ | 300℃ | 36℃ | 11℃ | 91.24% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 400℃ | 400℃ | 48℃ | 400℃ | 47℃ | 11℃ | 90.87% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 450℃ | 450℃ | 56℃ | 450℃ | 55℃ | 11℃ | 90.52% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 500℃ | 500℃ | 64℃ | 500℃ | 64℃ | 10℃ | 90.13% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 550℃ | 550℃ | 70 | 550℃ | 69℃ | 12℃ | 89.46% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 600℃ | 600℃ | 77℃ | 600℃ | 76℃ | 12℃ | 89.01% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 650℃ | 650℃ | 86℃ | 650℃ | 85℃ | 10℃ | 88.59% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 700℃ | 700℃ | 96℃ | 700℃ | 95℃ | 10℃ | 88.07% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 750℃ | 750℃ | 107 | 750℃ | 107℃ | 10℃ | 87.71% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 800℃ | 800℃ | 123℃ | 800℃ | 122℃ | 10℃ | 87.06% |
| Heat insulation test | cm | Actual measurement | 5*10 | 7 | 850℃ | 850℃ | 136℃ | 850℃ | 135℃ | 13℃ | 86.49% |
embodiment five:the thickness of corrosion resistant plate (6) is 2mm, the thickness of infrared reflection plate (7) is 1mm, the thickness of high sial cloth (8) is 0.7mm, the thickness of heat preserving ceramic cotton (9) is 50mm, the thickness of insulation zirconium aluminium cloth (10) is 0.8mm, the thickness of perforated plate (11) is 2mm, gross thickness is 55.7mm, then heat shield integral thickness is compressed to 50mm, test effect of heat insulation and the rate of heat dissipation of heat shield during heat shield internal temperature field difference 300 DEG C, 350 DEG C, 400 DEG C, 450 DEG C, 500 DEG C, 550 DEG C, 600 DEG C, and by stay-warm case mean coefficient of heat conductivity
calculation of thermal conductivity, see table 6.
Table 6
| Project | Unit | Data Source | Measuring point area | Insulation construction thickness | Heat source temperature | Burner hearth measuring point A temperature | Outer wall measuring point A temperature | Burner hearth measuring point B temperature | Outer wall measuring point B temperature | Environment temperature | Rate of heat dissipation |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 300℃ | 300℃ | 47℃ | 300℃ | 46℃ | 13℃ | 88.04% |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 400℃ | 400℃ | 65℃ | 400℃ | 64℃ | 13℃ | 87.14% |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 450℃ | 450℃ | 75℃ | 450℃ | 74℃ | 13℃ | 86.09% |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 500℃ | 500℃ | 85℃ | 500℃ | 84℃ | 13℃ | 84.66% |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 550℃ | 550℃ | 94℃ | 550℃ | 93℃ | 13℃ | 83.98% |
| Heat insulation test | cm | Actual measurement | 5*10 | 5 | 600℃ | 600℃ | 105℃ | 600℃ | 104℃ | 12℃ | 81.27% |
Sum up: the heat insulation effect of insulation material depends primarily on the thickness that insulation material coefficient of heat conductivity and insulation material lay, i.e. insulation layer thickness.Radiation loss increases with insulation layer thickness and reduces, but during actual use, heat-insulation layer is unsuitable blocked up, needs to consider coefficient of heat conductivity corresponding at different temperatures.Therefore, can draw from the contrast of table 4-table 6: table 7 is optimal selection, and this structure has best effect of heat insulation and radiating effect, makes gas turbine even running.
Table 7
| Material Name | Material thickness | Material density | Coefficient of heat conductivity | Rate of heat dissipation |
| Perforated plate | 1.2mm | Steel plate | 21.49 | 0 |
| Insulation zirconium aluminium cloth | 0.8mm | 0.42cm 3 | 19.17 | 7.3% |
| Heat preserving ceramic is cotton | 100mm | 0.80 | 62.7% | |
| High sial cloth | 0.7mm | 0.33cm 3 | 12 | 9.6% |
| Aluminium sheet | 1mm | Aluminium sheet | 0 | 14% |
| Corrosion resistant plate | 2mm | 304 steel plates | 0 | 0 |
Claims (1)
1. the assay method of the heat-proof quality of a gas turbine heat shield, described gas turbine heat shield adopts heat insulation layer structure, gas turbine heat shield from being followed successively by corrosion resistant plate (6), infrared reflection plate (7), high sial cloth (8), heat preserving ceramic cotton (9), insulation zirconium aluminium cloth (10) and perforated plate (11) outward to heat shield, and the assay method of its heat-proof quality is specific as follows:
1) make insulation cylindrical shell (1) and insulation closure plate (2), insulation cylindrical shell (1) and insulation closure plate (2) form airtight chamber, namely form gas turbine heat shield;
2) the upper installation two pairs of galvanic couple sockets (3) of insulation cylindrical shell (1), the often pair of galvanic couple socket (3) is placed in the inside and outside both sides of insulation cylindrical shell (1) respectively and position is corresponding, (3) are placed with galvanic couple with galvanic couple socket, and a pair galvanic couple is connected with a digital display type multi-point thermo detector (4) by wire;
3) be placed with electrothermal furnace in airtight chamber, electrothermal furnace is connected with the heating arrangement (5) inside and outside airtight chamber by wire;
4) this assay method is based on individual layer planomural steady heat conduction principle, the heat Q of individual layer planomural heat-insulation layer conduction:
Wherein, Q-heat-insulation layer heat conduction, W;
Qs-heat-insulation layer outer wall heat dissipation capacity, W;
λ-insulation material coefficient of heat conductivity ,/(m.k);
δ-insulation layer thickness, m;
F-perpendicular to the surface area of direction of heat flow, m
2;
F
wb-heat-insulation layer outer wall area, m
2;
T
wa-heat-insulation layer inner wall temperature, DEG C;
T
wb-heat-insulation layer outside wall temperature, DEG C;
T
0-environment temperature, DEG C;
the integrated heat transfer coefficient that-heat-insulation layer outer wall outwardly conducts heat, W/(m
2.k);
5) by changing the material of insulation material and changing the thickness of insulation material, and change heat shield internal temperature field, test the insulation material and insulation layer thickness thereof that can reach desirable heat insulation effect under various conditions;
6) the insulation data respectively under the above various condition of record also contrast, obtain heat insulation effect preferably and can satisfied temperature requirement insulation material and at different temperatures best insulation thickness after the match.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1060137A (en) * | 1990-09-28 | 1992-04-08 | 通用电气公司 | The heat-proof device of gas turbine space disc |
| CN1357739A (en) * | 2001-12-28 | 2002-07-10 | 北京科技大学 | Heat-insualting method and prepn. of combined heat insulating layer with great temperature gradient |
| CN1414216A (en) * | 2001-10-24 | 2003-04-30 | 三菱重工业株式会社 | Heat-insulating coating material and gas turbine component and gas turbine |
| CN2835566Y (en) * | 2005-11-11 | 2006-11-08 | 潍柴动力股份有限公司 | Thermal insulating cover for turbocharger |
| CN201106736Y (en) * | 2007-10-31 | 2008-08-27 | 刘智泉 | Heat-insulating layer capable of shielding radiating heat and convection heat |
| US7559142B2 (en) * | 2006-09-26 | 2009-07-14 | Pratt & Whitney Canada Corp. | Method of manufacturing a heat shield for a fuel manifold |
| CN202001385U (en) * | 2011-04-08 | 2011-10-05 | 上海超惠通风环保设备有限公司 | Thermal insulation structure of fan |
| CN202029374U (en) * | 2011-03-15 | 2011-11-09 | 苏州伊索来特耐火纤维有限公司 | Heat preservation cover of injection molding machine |
| CN102419342A (en) * | 2011-08-16 | 2012-04-18 | 上海建科检验有限公司 | Test device for detecting performance of heating surface of heat-insulating material |
-
2012
- 2012-05-16 CN CN201210151139.7A patent/CN102661972B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1060137A (en) * | 1990-09-28 | 1992-04-08 | 通用电气公司 | The heat-proof device of gas turbine space disc |
| CN1414216A (en) * | 2001-10-24 | 2003-04-30 | 三菱重工业株式会社 | Heat-insulating coating material and gas turbine component and gas turbine |
| CN1357739A (en) * | 2001-12-28 | 2002-07-10 | 北京科技大学 | Heat-insualting method and prepn. of combined heat insulating layer with great temperature gradient |
| CN2835566Y (en) * | 2005-11-11 | 2006-11-08 | 潍柴动力股份有限公司 | Thermal insulating cover for turbocharger |
| US7559142B2 (en) * | 2006-09-26 | 2009-07-14 | Pratt & Whitney Canada Corp. | Method of manufacturing a heat shield for a fuel manifold |
| CN201106736Y (en) * | 2007-10-31 | 2008-08-27 | 刘智泉 | Heat-insulating layer capable of shielding radiating heat and convection heat |
| CN202029374U (en) * | 2011-03-15 | 2011-11-09 | 苏州伊索来特耐火纤维有限公司 | Heat preservation cover of injection molding machine |
| CN202001385U (en) * | 2011-04-08 | 2011-10-05 | 上海超惠通风环保设备有限公司 | Thermal insulation structure of fan |
| CN102419342A (en) * | 2011-08-16 | 2012-04-18 | 上海建科检验有限公司 | Test device for detecting performance of heating surface of heat-insulating material |
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| CN102661972A (en) | 2012-09-12 |
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