CN105277291A - Combustion chamber wall temperature gradient measurement module - Google Patents
Combustion chamber wall temperature gradient measurement module Download PDFInfo
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- CN105277291A CN105277291A CN201410347169.4A CN201410347169A CN105277291A CN 105277291 A CN105277291 A CN 105277291A CN 201410347169 A CN201410347169 A CN 201410347169A CN 105277291 A CN105277291 A CN 105277291A
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Abstract
The present invention belongs to the field of the temperature measurement technology, and specifically relates to a nozzle section chamber wall temperature gradient measurement module of a liquid-propellant rocket engine combustion chamber. The module provided by the invention has an annular structure, and comprises an annular pressure plate, five thermocouple sensors, springs, separation blades, heat insulation linings and support sleeves. A disc-shaped separation blade is welded at each thermocouple sensor, one end, at the upper portion of the separation blade, of the each thermocouple sensor passes through a support sleeve and a spring, the support sleeves are sleeved with the springs and sleeved with the annular pressure plate, and the portions, below the separation blades, of the thermocouple sensors penetrate into the heat insulation linings. According to the invention, the temperature of the inner wall structure of the cooling channel in a cross section of the combustion chamber nozzle section may be measured, so that the parameters such as heat flow, gas wall temperature and outer wall temperature at the local place may be obtained.
Description
Technical field
The invention belongs to technical field of temperature measurement, be specifically related to a kind of Liquid Rocket Engine Combustion Chambers nozzle section chamber wall temperature gradiometry module.
Background technology
Working medium in Liquid Rocket Engine Combustion Chambers is the high-pressure gas of more than 3000K, in order to avoid locular wall generation ablative degradation, is provided with milling grooved tunnels between Inner Wall of Combustion Chamber and outer wall, introduces cryogen and cools chamber wall structure.The most high heat flux of firing chamber nozzle section locular wall can reach MW/m2 up to a hundred, the temperature difference that structured material bears often reaches more than hundreds of K, and violent along axially different position changes of heat flux, working environment is extremely severe, is the position that firing chamber the most easily occurs to lose efficacy.Therefore, the diabatic process found out in thrust chamber is carried out rational heat protection design thus ensures one of firing chamber reliably working and even the most important prerequisite improving engine performance.
The approach of firing chamber diabatic process research comprises heat test and simulation calculation, and both complement each other, and key is to obtain the valuable measurement data such as hot-fluid, gas wall temperature in Experimental Study of Heat Transfer.And due to rib width, the wall thickness all very thin (rib width is generally 1 ~ 2mm, and wall thickness generally only has 0.6 ~ 1mm) of groove milling formula cooling structure, be difficult to arrange that ordinary sensors is directly measured parameters such as heat flow density, gas wall temperatures in the structure.
The contracting of conventional amounts hot type can only obtain the mean heat flux in a certain section than firing chamber, and be subject to the impact of profile shrinkage expansion in firing chamber, hot-fluid diverse location change is vertically violent, hot-fluid vertically diverse location is not quite similar, so just cause mean heat flux accurately to reflect and actual work as geothermal heat flow, and owing to adopting sectioned water cooling body portion, coolant side structure, heat transfer conditions and full-scale phase difference are comparatively large, and the application error of this method measured value is larger.Although the method for immersioning thermocouple at inwall can directly record gas wall temperature, but because the degree of depth of the processing shallow slot burying thermopair generally reaches more than 0.5, and structure temperature change may to tens K on this depth direction, the gas wall temperature value accuracy recorded is not too high.And owing to needing to process through hole on inside and outside wall when inserting sensor, also need inner wall shallow rooved face copper electroplating layer to ensure sealing, not only complex process, and easily occur defect.The measurement of outer wall of combustion chamber temperature is in the past that according to the actual fact, affect by factors such as extraneous thermal environment, vibration environments, measurement result usually occurs there is the problem such as burr, distortion by measuring at outside wall surface spot welded hot galvanic couple.
Summary of the invention
The object of the present invention is to provide a kind of Liquid Rocket Engine Combustion Chambers nozzle section chamber wall temperature gradiometry module, cooling duct interior wall construction temperature in a certain xsect of firing chamber nozzle section can be measured, thus obtain the local parameter such as hot-fluid, gas wall temperature, outer wall temperature.
For achieving the above object, the technical solution used in the present invention is:
A kind of firing chamber chamber wall temperature gradiometry module, this module is loop configuration, comprises annular pressing plate, 5 thermocouple sensors, spring, catch, heat insulation housing, support sets; Often prop up thermocouple sensor temperature-sensitive end place and be all welded with disc catch, thermocouple sensor passes support set and spring in the one end on catch top, support set is inserted in spring, and be inserted in annular pressing plate in the lump, thermocouple sensor penetrates in heat insulation housing with lower part at catch.
Described annular pressing plate is partial circle plank frame, the two ends of partial circle are all processed with shape of a hoof breach along annulus radial direction, gap width n is larger than stud external diameter, inner side is semi-cylindrical, two breach semi-cylindrical center angle α, the plate body of each breach the same side process the tapped through hole of Md3 size; The radial blind holes that 5 axis angles are β, diameter is Ф d1 is evenly arranged between two shape of a hoof breach, blind hole depth is Ld1, the corresponding coaxial diameter in the bottom of each blind hole is the small through hole of Ф d2, and processes the groove of width d2 to the side of plate perpendicular to blind hole axis direction; D2 is larger than the thermocouple sensor diameter assembled, and d1 is larger than spring outer diameter, and Ld1 need be less than the length after spring-compressed; The stud first half is processed with screw thread, and bottom is inserted in the blind hole that outer wall of combustion chamber is processed, and is welded and fixed, and the angle after stud welding is α, identical with annular pressing plate two breach semi-cylindrical center angle.
Measured firing chamber processes 5 countersunk head blind holes on nozzle section outer wall and inwall, and the macropore in countersunk head blind hole is only arranged in outer wall; 5 blind hole centerlines are β, correspond to the center of adjacent 5 fins on inwall respectively; Blind hole depth controls to determine according to the distance L1 ~ L5 of bottom hole pitch from internal face, and L1, L2, L3, L4 are the arithmetic progression increased gradually.
L1, L2, L3, L4 are the arithmetic progression increased gradually, 0.4 ~ 0.8mm is got when ensureing that inwall is not penetrated, the value of L4 will ensure to be not more than 2mm in the interval that the measuring junction of corresponding thermocouple sensor is positioned at temperature and linearly changes with radial position.
The Design of length of described thermocouple sensor below catch becomes two kinds of sizes, and under L1 ~ L4 corresponding aperture catch, length is same size, and under L5 corresponding aperture catch, length is another size
When temperature measurement module is installed, first inserted by 5 thermocouple sensor temperature-sensitive ends in the aperture of countersunk head blind hole corresponding on outer wall of combustion chamber, heat insulation housing embeds in macropore; Then the groove being d2 by the width on annular pressing plate is in advance divided to penetrate in the through hole of diameter Ф d2 in the above thinner section of spring thermocouple sensor, then thermocouple sensor to be inserted in the lump in the blind hole Ф d1 on annular pressing plate with upper part at catch, and firmly press down annular pressing plate, spring is made to produce certain decrement, make stud be each passed through the shape of a hoof breach at its two ends simultaneously, then use nut to be screwed into stud and push down annular pressing plate; The masterpiece produced after spring-compressed makes the temperature-sensitive end of thermocouple sensor contact with the measured hole bottom surface on firing chamber for catch; For guaranteeing measurement effect, spring compression force is got 3 ~ 6N and is advisable, and decrement controls at 10 ~ 15mm, by annular pressing plate two ends shape of a hoof inner side semi-cylindrical and stud coordinate realize spacing; Use housing screw to be screwed in the Md3 threaded hole at annular pressing plate two ends, and compress stud.
Obtain hot-fluid, gas wall temperature, the outer wall temperature parameter at the tested position of nozzle section, firing chamber by the following method: to be put on by spring compression force on the probe-type micro thermocouple sensor that 5 length differ by annular pressing plate, make it to insert in the blind hole of different depth on the locular wall of firing chamber, record the temperature of position at the bottom of hole; Utilize the wall temperature data of the different depth directly recorded, use Fourier law to calculate the gentle wall temperature of hot-fluid; From Three-dimensional Heat-transfer Numerical Simulation Results, in distance gas wall 2mm distance, rib central temperature linearly reduces with the distance increase of distance gas wall; 4 thermocouple sensor temperature-sensitive ends to be arranged in this linear change interval and to be in different depth layer, obtaining one group of distance-temperature value (Li, Twi) (i=1,2,3,4); Organize data thus to carry out linear fit and obtain formula Twx=aL+Tw0: when L equals 0, Tw0 is gas wall temperature; In formula, the slope α of fitting a straight line equals thermograde, by the known heat flow density of Fourier law
in formula, λ is the coefficient of heat conductivity of solid wall material, and in temperature measurement module, measured value Tw5 is outer wall temperature value.
Beneficial effect acquired by the present invention is:
The present invention achieves the measurement of hot-fluid, gas wall temperature and outside wall temperature three parameters to a certain position of firing chamber nozzle section by a module, has the integration of height.Sensor to be circumferentially arranged in firing chamber perpendicular in a certain xsect of axis by annular pressing plate by the present invention, and measurement result is by the impact of the parameter such as hot-fluid, temperature along axis acute variation.The present invention utilizes spring compression force as thermopair snap-in force, fixing quantity to pretightning force can be realized by controlling decrement, to ensure that under heat test vibration environment thermocouple temperature sensitive end contacts with measured surface well and the stability of test data and validity.The present invention adopts stud installation, screw lock, detachably changes, have the advantage that structure is simple, easy to maintenance after arbitrary sensor degradation.To tested thrust chamber, the tiny blind hole of certain depth only need be processed on the locular wall of firing chamber, measurement requirement can be met, on the diabatic process of product and structural-load-carrying capacity impact little, cooling structure can design according to true firing chamber completely, can be used for full-scale or contracts than the diabatic process research of firing chamber.
Accompanying drawing explanation
Fig. 1 is firing chamber of the present invention chamber wall temperature gradiometry module 3-D view;
Fig. 2 is firing chamber of the present invention chamber wall temperature gradiometry module annular pressing plate vertical view;
Fig. 3 is firing chamber of the present invention chamber wall temperature gradiometry module annular pressing plate D-D cut-open view;
Fig. 4 is that firing chamber of the present invention chamber wall temperature gradiometry module installs rear view;
Fig. 5 is C direction view after firing chamber of the present invention chamber wall temperature gradiometry module is installed;
In figure: 1, nut; 3, stud; 4, thermocouple sensor; 5, heat insulation housing; 6, housing screw; 7, support set; 8, spring; 9, catch; 10, annular pressing plate; 11, outer wall; 12, inwall.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
As shown in Figure 1, Liquid Rocket Engine Combustion Chambers nozzle section chamber wall temperature gradiometry module of the present invention is loop configuration, comprises annular pressing plate 10,5 thermocouple sensors 4, spring 8, catch 9, heat insulation housing 5, support set 7, nut 1, stud 3, housing screws 6; Often prop up thermocouple sensor 4 temperature-sensitive end place and be all welded with disc catch 9, thermocouple sensor 4 passes support set 7 and spring 8 in the one end on catch 9 top, support set 7 is inserted in spring 8, and be inserted in annular pressing plate 10 in the lump, thermocouple sensor 4 penetrates in heat insulation housing 5 with lower part at catch 9.
As shown in Figures 2 and 3, annular pressing plate 10 is partial circle plank frame, the two ends of partial circle are all processed with shape of a hoof breach along annulus radial direction, gap width n is slightly larger than stud 3 external diameter, inner side is semi-cylindrical, two breach semi-cylindrical center angle α, the plate body of each breach the same side process the tapped through hole of Md3 size.The radial blind holes that 5 axis angles are β, diameter is Ф d1 is evenly arranged between two shape of a hoof breach, blind hole depth is Ld1, the corresponding coaxial diameter in the bottom of each blind hole is the small through hole of Ф d2, and processes the groove of width m (equaling d2) to the side of plate perpendicular to blind hole axis direction.D2 is slightly larger than thermocouple sensor 4 diameter assembled, and d1 is slightly larger than spring 8 external diameter, and Ld1 need be less than the length after spring 8 compression.
As shown in Figure 4, measured firing chamber needs processing 5 countersunk head blind holes on nozzle section outer wall 11 and inwall 12, and wherein, the macropore in countersunk head blind hole is only arranged in outer wall 11.5 blind hole centerlines are β, correspond to the center of adjacent 5 fins on inwall 12 respectively.Blind hole depth controls to determine according to the distance L1 ~ L5 of bottom hole pitch from internal face, L1, L2, L3, L4 are the arithmetic progression increased gradually, L1 value is little as far as possible, generally 0.4 ~ 0.8mm is got when ensureing that inwall is not penetrated according to machining precision, the value of L4 will ensure generally to be not more than 2mm in the interval that the measuring junction of corresponding thermocouple sensor 4 is positioned at temperature and linearly changes with radial position.
Stud 3 first half is processed with screw thread, and bottom is inserted in the blind hole of processing on outer wall of combustion chamber 11, and is welded and fixed, and the angle after stud 3 welds is α, identical with annular pressing plate 10 liang of breach semi-cylindrical center angles.
Fig. 4 and Fig. 5 be shown in by schematic diagram after the installation of annular temperature measurement module.As shown in Figure 4, when temperature measurement module is installed, first inserted by 5 thermocouple sensor 4 temperature-sensitive ends in the aperture of countersunk head blind hole corresponding on outer wall of combustion chamber 11, heat insulation housing 5 embeds in macropore.Then the groove being d2 by the width on annular pressing plate 10 is in advance divided to penetrate in the through hole of diameter Ф d2 in spring more than 8 thinner section thermocouple sensor 4, then thermocouple sensor 4 is inserted in the blind hole Ф d1 on annular pressing plate 10 at catch 9 with upper part (comprising spring 8, support set 7) in the lump, and firmly press down annular pressing plate 10, spring 8 is made to produce certain decrement, make stud 3 be each passed through the shape of a hoof breach at its two ends simultaneously, then use nut 1 to be screwed into stud 3 and push down annular pressing plate 10.The masterpiece that spring 8 compresses rear generation makes the temperature-sensitive end of thermocouple sensor 4 contact with the measured hole bottom surface on firing chamber for catch 9.For guaranteeing measurement effect, spring compression force is generally got 3 ~ 6N and is advisable, decrement general control at 10 ~ 15mm, by annular pressing plate 10 two ends shape of a hoof inner side semi-cylindrical and stud 3 coordinate realize spacing.Spring 8 rigidity can be determined according to the requirement of above-mentioned force of compression and decrement.As shown in Figure 5, cause annular pressing plate 10 to shake for preventing nut 1 generation in heat test process from loosening thus cause temperature-sensitive end in contact bad, using housing screw 6 to be screwed in the Md3 threaded hole at annular pressing plate 10 two ends, and compress stud 3.
Thermocouple sensor 4 is coordinated with the hole depth on inwall 12 according to outer wall of combustion chamber 11 mutually in the length of catch less than 9, is designed to two kinds of sizes, and under L1 ~ L4 corresponding aperture catch, length is same size, and under L5 corresponding aperture catch, length is another size.In this example, spring rate elects 0.335N/mm as, amount of spring compression controls at 15mm, the maximum difference of the amount of spring compression on the thermocouple sensor 4 of such insertion L1 ~ L4 corresponding aperture is at 1.2mm, the difference of the force of compression produced is 0.4N, stressed basically identical, and can to realize L1 ~ L4 respective sensor be same specification.
Obtain hot-fluid, gas wall temperature, the outer wall temperature parameter at the tested position of nozzle section, firing chamber by the following technical programs:
Adopt annular temperature measurement module, spring 8 force of compression put on the probe-type micro thermocouple sensor 4 that 5 length differ by annular pressing plate 10, make it to insert in the blind hole of different depth on the locular wall of firing chamber, record the temperature of position at the bottom of hole.Utilize the wall temperature data of the different depth directly recorded, use Fourier law to calculate the gentle wall temperature of hot-fluid:
From Three-dimensional Heat-transfer Numerical Simulation Results, in distance gas wall 2mm distance, rib central temperature linearly reduces with the distance increase of distance gas wall.Therefore, 4 thermocouple sensor 4 temperature-sensitive ends to be arranged in this linear change interval and to be in different depth layer, obtaining one group of distance-temperature value (Li, Twi) (i=1,2,3,4).Data can be organized thus carry out linear fit and obtain formula Twx=aL+Tw0: when L equals 0, Tw0 is gas wall temperature; In formula, the slope α of fitting a straight line equals thermograde, by the known heat flow density of Fourier law
in formula, λ is the coefficient of heat conductivity of solid wall material.In temperature measurement module, measured value Tw5 is outer wall temperature value.
Claims (7)
1. a firing chamber chamber wall temperature gradiometry module, it is characterized in that: this module is loop configuration, comprise annular pressing plate (10), 5 thermocouple sensors (4), spring (8), catch (9), heat insulation housing (5), support set (7); Often prop up thermocouple sensor (4) temperature-sensitive end place and be all welded with disc catch (9), thermocouple sensor (4) passes support set (7) and spring (8) in the one end on catch (9) top, support set (7) is inserted in spring (8), be inserted in annular pressing plate (10) in the lump, thermocouple sensor (4) penetrates in heat insulation housing (5) with lower part at catch (9).
2. firing chamber according to claim 1 chamber wall temperature gradiometry module, it is characterized in that: described annular pressing plate (10) is partial circle plank frame, the two ends of partial circle are all processed with shape of a hoof breach along annulus radial direction, gap width n is larger than stud (3) external diameter, inner side is semi-cylindrical, two breach semi-cylindrical center angle α, the plate body of each breach the same side process the tapped through hole of Md3 size; The radial blind holes that 5 axis angles are β, diameter is Ф d1 is evenly arranged between two shape of a hoof breach, blind hole depth is Ld1, the corresponding coaxial diameter in the bottom of each blind hole is the small through hole of Ф d2, and processes the groove of width d2 to the side of plate perpendicular to blind hole axis direction; D2 is larger than the thermocouple sensor assembled (4) diameter, and d1 is larger than spring (8) external diameter, and Ld1 need be less than the length after spring (8) compression; Stud (3) first half is processed with screw thread, bottom is inserted in the blind hole of the upper processing of outer wall of combustion chamber (11), and be welded and fixed, the angle after stud (3) welding is α, identical with annular pressing plate (10) two breach semi-cylindrical center angle.
3. firing chamber according to claim 2 chamber wall temperature gradiometry module, it is characterized in that: measured firing chamber is in nozzle section outer wall (11) and upper processing 5 the countersunk head blind holes of inwall (12), and the macropore in countersunk head blind hole is only arranged in outer wall (11); 5 blind hole centerlines are β, correspond to the center of adjacent 5 fins on inwall (12) respectively; Blind hole depth controls to determine according to the distance L1 ~ L5 of bottom hole pitch from internal face, and L1, L2, L3, L4 are the arithmetic progression increased gradually.
4. firing chamber according to claim 3 chamber wall temperature gradiometry module, it is characterized in that: L1, L2, L3, L4 are the arithmetic progression increased gradually, 0.4 ~ 0.8mm is got when ensureing that inwall is not penetrated, the value of L4 will ensure to be not more than 2mm in the interval that the measuring junction of corresponding thermocouple sensor (4) is positioned at temperature and linearly changes with radial position.
5. firing chamber according to claim 1 chamber wall temperature gradiometry module, it is characterized in that: described thermocouple sensor (4) becomes two kinds of sizes in catch (9) Design of length below, under L1 ~ L4 corresponding aperture catch, length is same size, and under L5 corresponding aperture catch, length is another size.
6. firing chamber according to claim 3 chamber wall temperature gradiometry module, it is characterized in that: when temperature measurement module is installed, first inserted by 5 thermocouple sensor (4) temperature-sensitive ends in the aperture of the upper corresponding countersunk head blind hole of outer wall of combustion chamber (11), heat insulation housing (5) embeds in macropore, then the groove being d2 by the width on annular pressing plate (10) is in advance divided to penetrate in the through hole of diameter Ф d2 in spring (8) above thinner section thermocouple sensor (4), then thermocouple sensor (4) to be inserted in the lump in the blind hole Ф d1 on annular pressing plate (10) with upper part at catch (9), and firmly press down annular pressing plate (10), spring (8) is made to produce certain decrement, make stud (3) be each passed through the shape of a hoof breach at its two ends simultaneously, then use nut (1) to be screwed into stud (3) and push down annular pressing plate (10), the masterpiece produced after spring (8) compression makes the temperature-sensitive end of thermocouple sensor (4) contact with the measured hole bottom surface on firing chamber for catch (9), for guaranteeing measurement effect, spring compression force is got 3 ~ 6N and is advisable, and decrement controls at 10 ~ 15mm, by annular pressing plate (10) two ends shape of a hoof inner side semi-cylindrical and stud (3) coordinate realize spacing, use housing screw (6) to be screwed in the Md3 threaded hole at annular pressing plate (10) two ends, and compress stud (3).
7. firing chamber according to claim 1 chamber wall temperature gradiometry module, it is characterized in that: obtain hot-fluid, gas wall temperature, the outer wall temperature parameter at the tested position of nozzle section, firing chamber by the following method: spring (8) force of compression put on the probe-type micro thermocouple sensor (4) that 5 length differ by annular pressing plate (10), make it to insert in the blind hole of different depth on the locular wall of firing chamber, record the temperature of position at the bottom of hole; Utilize the wall temperature data of the different depth directly recorded, use Fourier law to calculate the gentle wall temperature of hot-fluid; From Three-dimensional Heat-transfer Numerical Simulation Results, in distance gas wall 2mm distance, rib central temperature linearly reduces with the distance increase of distance gas wall; 4 thermocouple sensor (4) temperature-sensitive ends to be arranged in this linear change interval and to be in different depth layer, obtaining one group of distance-temperature value (Li, Twi) (i=1,2,3,4); Organize data thus to carry out linear fit and obtain formula Twx=aL+Tw0: when L equals 0, Tw0 is gas wall temperature; In formula, the slope α of fitting a straight line equals thermograde, by the known heat flow density of Fourier law
in formula, λ is the coefficient of heat conductivity of solid wall material, and in temperature measurement module, measured value Tw5 is outer wall temperature value.
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| CN108801487A (en) * | 2018-04-17 | 2018-11-13 | 李傲兰 | A kind of metal specimen temperature measuring equipment and system |
| CN109012529A (en) * | 2018-06-05 | 2018-12-18 | 佛山科学技术学院 | Can stably measured temperature the cold well of light-catalyzed reaction instrument |
| CN112393815A (en) * | 2020-12-09 | 2021-02-23 | 太原理工大学 | Method for testing transient temperature field of friction surface of large-diameter fluid viscous clutch |
| CN113188155A (en) * | 2021-05-07 | 2021-07-30 | 南京航空航天大学 | Backflow combustion chamber for wall temperature distribution measurement based on thermocouple |
| CN113776846A (en) * | 2021-09-10 | 2021-12-10 | 西安航天动力研究所 | Device and method for measuring real-time heat flux density of wall surface of combustion chamber |
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