CN101608953B - Method and device for measuring temperature and heat flow distribution on internal face of combustion chamber - Google Patents
Method and device for measuring temperature and heat flow distribution on internal face of combustion chamber Download PDFInfo
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- CN101608953B CN101608953B CN2008101152665A CN200810115266A CN101608953B CN 101608953 B CN101608953 B CN 101608953B CN 2008101152665 A CN2008101152665 A CN 2008101152665A CN 200810115266 A CN200810115266 A CN 200810115266A CN 101608953 B CN101608953 B CN 101608953B
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Abstract
The invention relates to a method and a device for measuring temperature and heat flow distribution on the internal face of a combustion chamber, and belongs to the field of temperature and heat flow measurement. The measurement device comprises the combustion chamber, a temperature sensor, a temperature sensor fixing device, a signal transmission line and a computer; the lateral surface of the combustion chamber is provided with a series of equidistant temperature measuring blind holes; the temperature sensor measures the temperatures of the bottoms of the blind holes so as to obtain a temperature output curve of each measure point; and then a certain value computational method is adopted to calculate the temperature and the heat flow distribution on the internal face of the combustion chamber. Due to adopting a proposal of measuring the temperatures of the blind holes, the method and the device solve the problems of high processing and mounting difficulties, inconvenient detachment and the like in the prior art; and the armored thermocouple temperature sensor with mature technology is adopted, so that the cost is low and the use is convenient. The method and the device can be used for measuring the temperature and the heat flow distribution on the internal face of a combustion device with an axial symmetry structure.
Description
[technical field]
The present invention relates to a kind of measuring method and device that is used to obtain firing chamber inner wall temperature and heat flux distribution.Inner wall temperature and heat flux distribution when the present invention is used in particular for obtaining rocket engine axially symmetric structure firing chamber steady operation.
[background technology]
In the development process of rocket chamber, in order to obtain good thermal protection effect, the heat transfer characteristic of firing chamber, i.e. the distribution of internal face temperature and hot-fluid is one of high spot reviews content.
In the research to the firing chamber heat transfer characteristic, the general employing held the hot type chamber structure, and test period is arranged on several seconds, and the measurement of employing temp sensor device obtains firing chamber internal face temperature and heat flux distribution is a method commonly used in the rocket engine test.In the rotational symmetry chamber structure,, can represent whole circumferential heat transfer situation as long as obtain the internal face temperature of a circumferential direction of combustion chamber wall surface and the distribution of hot-fluid.Upwards on different axial positions, arrange abundant point for measuring temperature in same week, can investigate the distribution situation of internal face temperature and hot-fluid fully.
The general measuring method that obtains internal face temperature and hot-fluid; One group of thermopair and one group of heat flow meter have been adopted respectively; Their gauge head is all placed on the inwall of firing chamber, with direct acquisition firing chamber inner wall temperature and hot-fluid, for example WilliamM.Marshall '; Sibtosh Pal ', etc. " Benchmark Wall Heat Flux Data for a GO
2/ GH
2SingleElement Combustor " .AIAA 2005-3572 is said.But heat flow meter in this method causes unavailable owing to can't isolate with ground signal.A kind of coaxial-type temperature sensor has been adopted in the measurement of internal face hot-fluid, and it has two temperature measuring heads, and one is installed on internal face, directly measures inner wall temperature, and one is installed on same axial position apart from the internal face certain distance.Employing measures these 2 temperature and calculates acquisition inner surface heat flow valuve.This method is owing to directly place thermopair on the inwall; Therefore will make the temperature that records is true inner wall temperature; Then the TEMP modulator material must be identical with locular wall; Sensor temperature measuring head shape must be coincide with inwall circular arc shape, and whole coaxial-type thermopair closely contacts, combines together with the firing chamber locular wall.This scenario-frame is complicated, and processing, installation and sealing are difficult, must adopt a kind of coaxial-type temperature sensor of complicacy, the cost height, and sensor material is not optional, and it is limited to measure range, and sensor is also on-dismountable.Under the situation that the firing chamber size changes, need new thermocouple assembly.
[summary of the invention]
The purpose of this invention is to provide a kind of measuring method that obtains firing chamber internal face temperature and hot-fluid simply, reliably.The problem that the present invention will solve is adopt the triumphant dress formula thermopair of technology maturation that wall is carried out thermometric, and thermopair conveniently to carry out dismounting; Body portion adopts the blind hole scheme in the firing chamber, and point for measuring temperature is positioned at the bottom of the hole, solves firing chamber processing, the difficulty that seals is installed; Adopt a kind of thermopair fastener, realize the thermopair location, and temperature measuring head is closely contacted with point for measuring temperature; Axially only adopting the single-point thermometric on the each point, adopt a kind of data processing method to obtain internal face temperature and heat flow data.
A kind of firing chamber internal face temperature and heat flux distribution measuring method comprise firing chamber, thermocouple temperature sensor, thermocouple fixing device (comprising clamp nut and screw), signal transmssion line, computing machine and a kind of Heat Transfer Calculation and program.Same week of firing chamber body portion upwards is drilled with and equidistantly distributes thermometer hole vertically; Thermometer hole is a blind hole; Be the less plane of area at the bottom of each hole, hole, and it is interior for measuring a point for measuring temperature hole of head of combustion chamber temperature to remove the spray panel, all the other thermometer holes are identical apart from firing chamber inwall distance; What temperature sensor adopted is triumphant dress formula thermocouple temperature sensor; Temperature sensor stretches into thermometer hole, adopts thermocouple fixing device that thermopair is fixed on the firing chamber, and its temperature measuring head is closely contacted with at the bottom of the hole; Said temperature sensor clamping device comprises clamp nut and screw; In working time, the temperature signal that collects measuring point is sent in the computing machine through signal transmssion line in the firing chamber, obtains each measuring point temperature survey curve of output; Utilize the temperature survey curve of output of each measuring point, be divided into the distribution that following three steps obtain internal face temperature and hot-fluid:
The first step: because sensor has certain response time, according to its response characteristic measurement output temperature curve is carried out match and resolve the method for finding the solution again, obtain the temperature rising curve of true point for measuring temperature;
Second step:, choose and stop temperature constantly with calculating computing time according to the test pressure curve;
The 3rd step: at first carry out the iterative computation of one-dimensional and unsteady state heat conduction, obtain the initial value that two dimension is calculated the internal face each point, the iterative computation of carrying out two-dimensional axisymmetric unstable state heat conduction again obtains the distribution of firing chamber internal face temperature and hot-fluid.
Advantage and good effect that the measuring method of the gentle heat flux distribution of firing chamber of the present invention inwall has are: triumphant dress formula thermocouple temperature sensor commonly used, technology maturation has been adopted in (1); Cost is low; Processing is simple, and is easy to use, can freely select thermocouple material; (2) on the firing chamber, adopted the blind hole scheme, avoided measuring the firing chamber of bringing and processed, install problems such as sealing; (3) adopted thermocouple fixing device, thermopair is closely contacted with at the bottom of the blind hole hole; (4) sensor installation and removal easily; (4) realized that only carrying out the single-point thermometric at same circumferential position gets final product; (5) this method has range of application comparatively widely, highly versatile.Can be applied to one-jet and multi-jet researchs such as liquid, gaseous propellant, and can be generalized to the heat of measuring the jet pipe part fully and carry, can also be applied in other development test that need obtain heat transfer characteristic.
[description of drawings]
Fig. 1 is the firing chamber scheme of installation of band measurement mechanism
Fig. 2 is a clamp nut
Fig. 3 is a screw
Fig. 4 is single measured hole measurement mechanism scheme of installation
Fig. 5 is type testing chamber pressure and certain point for measuring temperature temperature output curve diagram
Fig. 6 is the temperature sensor characteristic curve synoptic diagram
Fig. 7 is sensor curve of output and true temperature curve contrast synoptic diagram
Fig. 8 is that temperature curve transforms instance
Fig. 9 is the one dimension computation model
Figure 10 is the continuity distribution boundary condition synoptic diagram of the coefficient of heat transfer
[embodiment]
Further specify the present invention below in conjunction with accompanying drawing with embodiment.
Implementing this measuring method equipment therefor mainly comprises: firing chamber body portion 1, thermocouple temperature sensor 2 and the thermocouple fixing device of band thermometer hole (comprising clamp nut 3 and screw 4).Before the experiment thermocouple probe is stretched in the thermometer hole, probe is closely contacted with the solid wall surface point for measuring temperature, thermocouple location is fixed with thermocouple fixing device.Can collect inner each the measuring point temperature of chamber wall in the experiment.
As shown in Figure 1, thermometer hole is line spread vertically, and except that head one point for measuring temperature, each thermometer hole degree of depth, diameter, structure are identical.Thermometer hole is coaxial stepped hole structure, and the hole Bottom Shape is the plane, and the apertura lateralis diameter is greater than inboard aperture, and apertura lateralis has internal thread segment.
As shown in Figure 2, sensor clamp nut 3 the latter halfs are external thread structure, and the first half is a solid cylinder, and there is internal thread hole the right cylinder side, have diameter to be a bit larger tham the through hole of thermopair external diameter on the right cylinder central shaft, and this through hole and side threaded hole connect.During experiment; Clamp nut 3 the latter half external threads are fixed on the engine chamber 1 thermometer hole internal thread; The through hole that sensor 2 thermometric ends pass clamp nut 3 central shaft positions makes temperature measuring head contact with measuring point; Screw 4 screws in from clamp nut 3 side threaded holes sensor 2 thermometric ends is fixed, and the sensor temperature measuring head is closely contacted with point for measuring temperature, and the sensor installation diagram is as shown in Figure 4.
Adopt above temperature measuring equipment that the research of heat transfer characteristic has been carried out in the firing chamber of being studied, type testing chamber pressure and point for measuring temperature temperature sensor curve of output are as shown in Figure 5.
Being treated to the gentle inwall hot-fluid of inwall to these temperature curves need be through three process, as follows.
1, measuring temperature inversion is actual wall temperature
Because thermopair has certain response characteristic, promptly establishes initial temperature t
0Thermopair constantly suddenly constant temperature object (T) is measured 0, the response curve of thermocouple measuring temperature t is:
τ wherein
cBe the time constant of thermopair, τ is a time quantum, and thermocouple measurement constant temperature object temperature output qualitative curve is illustrated in fig. 6 shown below.
And chamber wall temperature is the unsteady-state heat transfer process in process of the test, and the locular wall temperature is the curve that constantly rises, and the existence of time constant causes having certain difference between thermopair curve of output and the true wall temperature curve.And along with the rising of true wall temperature, the gap between thermopair curve of output and the true wall temperature is increasing, and this is because the existence of response constant causes the rate of rise of curve of output to be lower than true rate of rise forever, and is as shown in Figure 7.
This difference is directly related with responsive time constant.This paper adopts and earlier the thermometric curve of output is carried out curve fitting, and the method for again equation (1) being resolved is carried out the temperature correction.Below lift an actual thermometric curve as example, like Fig. 8.T1 is that curve is gathered in heat run among the figure, and T2 has considered the temperature curve behind the thermal response time of sensor by 4 order polynomial matched curves (T2 is covered by T1), T3, and time constant is 100ms.
2, choose the temperature that computing time and calculating stop the moment
Fig. 5 is the chamber pressure curve of certain type testing and the temperature curve of output of certain measurement point.Ignore the start-up course influence of conducting heat in the data processing, think that pressure is established to 90% of steady pressure and is the burning beginning, this be since this moment flow field the hot-fluid of inwall has been set up basically, like t0 among Fig. 5 constantly.The calculating termination time is taken as the stable end point time location of chamber pressure, and like t1 among Fig. 5 constantly, the temperature of choosing each this moment of measuring point stops temperature constantly as calculating.
3, calculate inwall hot-fluid and interior wall temperature
Each axially goes up measurement point temperature value T existing known n group
1, T
2..., T
N-1, T
nJust can calculate the gentle heat flow value of inwall of each axial location.
In the calculating, what tried to achieve is whole test time internal face average heat transfer coefficient.Owing to only arranged a measurement point in the spray panel, established even hot the carrying that be on the whole spray panel in the calculating; Try to achieve axially and the same footpath of the measurement point inwall each point average heat transfer coefficient that makes progress, axially go up between the each point and obtain with linear interpolation.Calculation procedure divided for two steps carried out, the following introduction.
The first step is calculated integrated heat transfer coefficient h on each axial location
kIterative initial value.
, two-dimension unsteady state adopt one-dimensional and unsteady state to calculate falling of two dimension calculating before falling generation calculating for initial value.Suppose not have between each measurement point heat transmission, the inwall hot-fluid is merely one dimension heat conduction radially, like Fig. 9.
The combustion gas stagnation temperature is got propellant heating power is calculated adiabatic combustion temperature T
*, rule of thumb choose two close coefficient of heat transfer h
K1, h
K2(h
K1＜h
K2) one-dimensional model is carried out unstable state calculating, be selected test period length computing time.Adopt one dimension rotational symmetry conduction model, the spray panel is in the model side loaded, and body portion loads at inwall.Obtain calculating termination measurement point position two temperatures value T constantly
K1, T
K2, with measured value T
kCarrying out linear interpolation directly obtains and falls for initial value h
k
In second step, adopt rotational symmetry unstable state heat conduction to calculate inwall each point temperature and hot-fluid.
The employing axisymmetric model calculates, like Figure 10.Each h that utilizes the first step to obtain
k(k=1,2 ..., n) value is calculated as being carried in the borderline third boundary condition of rotational symmetry unstable state conduction model, adopts following continuity space boundary condition, and wherein the spray panel adopts evenly hot carrying, and body portion adopts the linear interpolation of each point to load.All the other each faces all adopt adiabatic boundary condition.The rerum natura of red copper material is carried out interpolation processing with temperature.
Calculating starting condition is that red copper is the environment temperature T of testing laboratory
0, thermal boundary condition adopts step to load on the time, and be test period computing time, and rotational symmetry unstable state heat conduction equation is following.
Source item
Get 0 in the cylindrical section internal point, on the border, get h
k(T
*-T0
k), T0 wherein
k(k=1,2 ..., n) be interior wall temperature.Result of calculation will obtain each measurement point of n group and calculate the temperature value T that stops the moment
k' (k=1,2 ..., n).
Compare T
k' and each point measured value Tk, there is certain difference in the general Tk ' that calculates for the first time with Tk, chooses h again
k'=h
k(T
k-T
0)/(T
k'-T
0) calculate, in the permissible error scope, stop to calculate up to each measurement point temperature value that calculates and measured value error.Interior vertically wall temperature of output spray panel this moment and body portion and hot-fluid.
Claims (9)
1. the measurement mechanism of firing chamber internal face temperature and heat flux distribution; Comprise firing chamber, thermocouple temperature sensor, thermocouple fixing device, signal transmssion line, computing machine; The thermometer hole that equidistantly distributes is vertically arranged to have in the side, firing chamber; Thermocouple temperature sensor stretches into the temperature measuring head that makes the thermometric end in the thermometer hole and contacts with measuring point, with thermocouple fixing device thermocouple temperature sensor is fixed, and the temperature signal that thermocouple temperature sensor collects measuring point is sent in the computing machine through signal transmssion line; Obtain measuring point temperature curve of output; It is characterized in that: the thermopair that is adopted is the triumphant dress formula thermopair of technology maturation commonly used, and said thermometer hole is a blind hole, and thermocouple temperature sensor is fixed on the firing chamber by dismountable thermocouple fixing device.
2. the measurement mechanism of firing chamber according to claim 1 internal face temperature and heat flux distribution is characterized in that: said thermometer hole is a stepped hole, and the hole Bottom Shape is the plane, and there is one section threaded hole the thermometer hole outer end.
3. the measurement mechanism of firing chamber according to claim 1 internal face temperature and heat flux distribution is characterized in that: the thermometer hole, the inwall distance equates all the other thermometer holes said thermometer hole apart from the firing chamber in the spray panel.
4. the measurement mechanism of firing chamber according to claim 1 internal face temperature and heat flux distribution is characterized in that: said thermocouple fixing device comprises clamp nut and screw.
5. the measurement mechanism of firing chamber according to claim 4 internal face temperature and heat flux distribution is characterized in that: said clamp nut one end is an external thread section.
6. the measurement mechanism of firing chamber according to claim 4 internal face temperature and heat flux distribution is characterized in that: on the said clamp nut axis through hole is arranged, this through-hole diameter is slightly larger than thermocouple temperature sensor thermometric section external diameter.
7. the measurement mechanism of firing chamber according to claim 6 internal face temperature and heat flux distribution is characterized in that: there is a threaded hole said clamp nut side, and through hole connects on this threaded hole and the axis.
8. the measurement mechanism of firing chamber according to claim 7 internal face temperature and heat flux distribution; It is characterized in that: thermocouple temperature sensor passes that through hole stretches in each thermometer hole on the clamp nut axis; Its temperature measuring head and thermometer hole diapire face are adjacent to, and in the internal thread of the thermometer hole of clamp nut male end screw-in side, firing chamber, screw screws in the screw thread of clamp nut side and compresses thermocouple temperature sensor thermometric section; Fixation of sensor thermometric section makes temperature measuring head closely contact with measuring point.
9. method with the described measurement device of claim 1 firing chamber internal face temperature and heat flux distribution is characterized in that: after obtaining each point for measuring temperature temperature curve of output through experiment, be divided into the distribution that following three steps obtain internal face temperature and hot-fluid:
The first step: because thermocouple temperature sensor has certain response time, according to its response characteristic each point for measuring temperature temperature curve of output is carried out match and resolve the method for finding the solution again, obtain the temperature rising curve of true point for measuring temperature;
Second step:, choose and stop temperature constantly with calculating computing time according to the test pressure curve;
The 3rd step: at first carry out the iterative computation of one-dimensional and unsteady state heat conduction, obtain the initial value that two dimension is calculated the internal face each point, the iterative computation of carrying out two-dimensional axisymmetric unstable state heat conduction again obtains the distribution of firing chamber internal face temperature and hot-fluid.
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| CN111413003A (en) * | 2020-03-23 | 2020-07-14 | 天津大学 | Sound velocity nozzle pipe wall thermal field distribution measuring system |
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| EP4116545A1 (en) * | 2021-07-05 | 2023-01-11 | Siemens Energy Global GmbH & Co. KG | Continuous flow engine measurement arrangement |
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