CN212082681U

CN212082681U - Device for accurately measuring temperature rise efficiency of compressor stage

Info

Publication number: CN212082681U
Application number: CN202020129972.1U
Authority: CN
Inventors: 马宏伟; 肖安琪
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2020-01-20
Filing date: 2020-01-20
Publication date: 2020-12-04
Anticipated expiration: 2030-01-20

Abstract

The invention belongs to the technical field of turbine testing, and particularly relates to a device for accurately measuring the temperature rise efficiency of a compressor stage. After the measuring device is calibrated through the calibration wind tunnel, a calibration curve can be obtained; in actual measurement, based on data measured by five pressure measuring holes and a temperature sensor, total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, pitch angle, speed and density parameters of a measured three-dimensional steady-state flow field can be simultaneously obtained through data processing according to a calibration coefficient curve and a formula obtained by calibrating a calibration wind tunnel, the service life of the temperature sensor is prolonged, the insensitive angle range of airflow is widened, and the measurement spatial resolution and the measurement precision are improved; the measuring method can accurately measure the temperature rise efficiency of the single stage of the multistage compressor by optimizing the measuring point layout and the quality weighting averaging method.

Description

Device for accurately measuring temperature rise efficiency of compressor stage

Technical Field

The invention belongs to the technical field of turbine testing, and particularly relates to a device for accurately measuring the temperature rise efficiency of a compressor stage, which can accurately measure the temperature rise efficiency of a turbine compressor single stage on the premise of weakening the interference on a measured flow field to the maximum extent.

Background

The turbine is a complex machine, the compressor is one of the main components of the turbine, and the temperature rise efficiency of the compressor directly determines the overall efficiency of the turbine, so that the continuous improvement of the temperature rise efficiency of the compressor is an important way for developing the turbine technology. The temperature rise efficiency of the compressor is improved, firstly, accurate measurement needs to be carried out on the temperature rise efficiency, and the measurement error of the prior art is too large and exceeds the value of the efficiency improvement of the compressor.

The calculation formula of the temperature rise efficiency of the gas compressor is as follows:

in the formula:

-total inlet temperature of test compressor, K

-total temperature of outlet of test compressor, K

For testing the total pressure Pa of the outlet of the compressor

For testing total pressure Pa at inlet of compressor

Gamma-specific heat ratio

According to the formula, in order to measure the temperature rise efficiency of the compressor, the total inlet temperature of the compressor to be tested needs to be measured

Total outlet temperature

Inlet total pressure

Total pressure at the outlet

When the total temperature of an inlet is measured by the existing measuring method, only a measuring point is arranged at the position with the lowest airflow speed in an air intake system. However, at the inlet position, the flow field also has unevenness, and the influence caused by the unevenness can be ignored when only one measuring point is used for measuring, so that the final measuring error is increased.

When the total temperature of an outlet is measured by the conventional measuring method, a rake-shaped total temperature probe or 6-8 multipoint total temperature probes are used for measuring the temperature of the outlet. And calculating the average value of the total outlet temperature by an arithmetic average method. And when calculating each measured temperature, selecting a corresponding temperature recovery coefficient according to the form of the temperature probe. In the outlet flow field, the flow velocity of each point is not uniform, and the average value of the total temperature of the outlet calculated by an arithmetic average method ignores the nonuniformity, so that the measurement error is increased.

When the total pressure of an inlet is measured by the conventional measuring method, the total pressure of the inlet is measured by four multipoint total pressure probes, and the average value of the total pressure of the inlet is calculated by an area averaging method. Due to the nonuniformity of flow field flow velocity, extra calculation errors can be brought by using an area averaging method to calculate the total pressure average value, and the precision of the whole test is further reduced.

When the total pressure of an outlet is measured by the conventional measuring method, three modes are available: (1) when one rake-shaped total pressure probe or a plurality of (10-12) multipoint total pressure probes are moved along the radial direction to measure the total pressure of the outlet, the multipoint and the plurality of total pressure probes are arranged along the circumferential direction, and the total pressure non-uniformity factor in the grid distance direction is considered. And (2) driving the single-point combined probe to measure the total pressure in a sector covering 1.2 times of the grid distance by using a displacement mechanism or a rotating case. (3) And measuring the total pressure of the outlet by using a plurality of rake-shaped total pressure probes, wherein each rake-shaped total pressure probe is respectively arranged on the average radius of the isotorus of the measured cross section of the outlet. The problem of uneven flow velocity of each point is also ignored in the total pressure measurement mode, and further the measurement error is increased.

The existing measurement can only measure parameters of an inlet and an outlet of a multi-stage compressor but can not measure parameters of an interstage of the multi-stage compressor, so that for the multi-stage compressor, the existing technology can only measure the overall efficiency of the multi-stage compressor but can not measure the single-stage efficiency of the compressor.

Most of the existing temperature measuring devices are designed according to the requirement that a temperature sensor is over against a main stream, the head of the temperature measuring device adopts a stagnation cover structure to collect incoming flow, and the temperature sensor is placed in the stagnation cover; secondly, the strength of the sensor is generally improved by increasing the size of the temperature sensor, and the size of the stagnation cover is added, so that the size of the measuring device is large, and the spatial resolution of the measuring device is poor; thirdly, the insensitive angle of the airflow is small, and when the deflection angle of the incoming flow to be measured is large, the airflow cannot be fully stagnated, so that the surface heat exchange of the temperature sensor is insufficient, and the total temperature measurement error is large.

In addition, when the existing measuring device measures parameters of the air compressor, a single pressure measuring device and a single temperature measuring device are mostly used for measuring the pressure and the temperature respectively, so that the pressure and the temperature cannot be measured at the same point at the same time, the measured parameters do not come from the same streamline, the flow in the air compressor has strong non-regularity and spatial non-uniformity, and the final measured result generates extra errors. In addition, when the probe extends into the flow field of the compressor for measurement, the interference to the measured flow field is inevitably generated, and in the prior art, due to the fact that the single pressure measuring device and the single temperature measuring device are adopted for measurement, the used probe is excessive in number, the large interference to the measured flow field is generated, and finally the measurement error is increased.

Therefore, the existing measuring device and the measuring method thereof cannot meet the requirement of accurate measurement of the temperature rise efficiency of the compressor, and a device for accurately measuring the temperature rise efficiency of the compressor stage is urgently needed to realize accurate measurement of the temperature rise efficiency of the compressor.

Disclosure of Invention

The device for accurately measuring the temperature rise efficiency of the compressor stage is different from the conventional single pressure measuring device and temperature measuring device, is a pressure and temperature combined measuring device, and can realize the full-parameter measurement of the total temperature, the total pressure, the static temperature, the static pressure, the Mach number, the deflection angle, the pitch angle, the speed and the density of the air flow through a single device. The device of the invention abandons the design idea of the traditional total temperature measuring device, and based on years of research of the applicant, the invention creatively provides the layout and the structural design of placing the temperature sensor on the leeward side of the head of the probe, thereby effectively reducing the impact of the air flow on the temperature sensor, oil drops, dust and the like mixed in the air flow on the temperature sensor and prolonging the service life of the temperature sensor; the size of the head of the measuring device is effectively reduced, and the spatial resolution of the measuring device is improved; the convection heat transfer between the air flow and the temperature sensor is enhanced, and the temperature recovery coefficient is high and stable within a larger deflection angle range.

The device for accurately measuring the temperature rise efficiency of the compressor stage is different from the conventional measuring method. In the existing method, a single temperature measuring device and a pressure measuring device are used for respectively measuring the total temperature and the total pressure of an inlet and an outlet of the air compressor, and the device measuring method in the invention utilizes the measuring device in the invention to carry out multi-parameter synchronous measurement, thereby reducing the number of the measuring devices and simplifying the test process. In the prior art, after the total temperature and total pressure parameters of the test point are obtained, the total temperature and total pressure of the measured section are obtained by an arithmetic average or area average method. For the multi-stage compressor, the existing measuring method can only measure the whole temperature rise efficiency, but the device measuring method in the invention can measure the one-stage temperature rise efficiency of the multi-stage compressor through a new measuring section and measuring point layout.

The invention provides a device for accurately measuring the temperature rise efficiency of a compressor stage, which aims to solve the technical problems that: firstly, the existing measuring device cannot simultaneously measure all parameters of a flow field such as total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, pitch angle, speed, density and the like; secondly, the existing temperature measuring device has the problems of low total temperature recovery coefficient, small insensitive angle, easy damage of a temperature sensor and short service life; thirdly, the existing measuring method can not realize simultaneous multi-parameter simultaneous same-point measurement, and the problem of excessive use of measuring devices is solved; fourthly, the problem that the results of measuring the total temperature and the total pressure of the cross section obtained by the existing measuring method are inaccurate; fifthly, the problem that the existing measuring method cannot realize the measurement of the temperature rise efficiency of the middle stage of the multi-stage compressor.

The technical scheme of the invention is as follows:

the utility model provides a device for accurate measurement compressor level temperature rise efficiency, by device head (1), device branch (2), temperature sensor (3), adiabatic insulating mounting (4), temperature sensor cable draw-out passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), pressure measurement upper punch (9), pressure measurement lower punch (10), pressure measurement pipe passageway (11), temperature sensor cable (12), pressure measurement pipe (13), leading flank (14), trailing flank (15), the positive four prismatic table top surface of indent (16), the positive four prismatic table left surface of indent (17), the positive four prismatic table right flank of indent (18), the positive four prismatic table upper flank of indent (19), the positive four prismatic table downside of indent (20) are constituteed, its characterized in that: the device head (1) is a cylinder, the windward side is a front side (14), an inwards concave regular quadrangular frustum top surface (16), an inwards concave regular quadrangular frustum left side surface (17), an inwards concave regular quadrangular frustum right side surface (18), an inwards concave regular quadrangular frustum upper side surface (19) and an inwards concave regular quadrangular frustum lower side surface (20), the leeward side is a rear side surface (15), the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively arranged on the inwards concave regular quadrangular frustum top surface (16), the inwards concave regular quadrangular frustum left side surface (17), the inwards concave regular quadrangular frustum right side surface (18), the inwards concave regular quadrangular frustum upper side surface (19) and the inwards concave regular quadrangular frustum lower side surface (20), and the rear side surface (15) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);

furthermore, the diameter of a cylinder of the head part (1) of the device is 2-8 mm, the height of the cylinder is 5-30 mm, 5 circular pressure leading pipe channels (11) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other are axially arranged in the head part of the device, the 5 circular pressure leading pipe channels (11) are respectively communicated with the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) and are respectively communicated with five pressure leading pipes (13) which are packaged at the joint of the head part of the device (1) and the device supporting rod (2), and the tail parts of the device supporting rod (2) are led out through the pressure leading pipe channels (11) in the device supporting rod (2);

furthermore, the front side surface (14) of the head part (1) of the device is provided with an inwards concave regular quadrangular frustum, the upper edge of the top surface (16) of the inwards concave regular quadrangular frustum is vertical to the cylindrical axis of the head part (1) of the device, the length is 0.5-3 mm, the distance between the top surface (16) of the inwards concave regular quadrangular frustum and the cylindrical axis of the head part (1) of the device is 0.5-2 mm, and is not more than 0.25 times of the diameter of the cylinder of the head part (1), the cylindrical surface of the head part (1) of the bottom surface of the inwards concave regular quadrangular frustum is tangent, and the included angle between the bottom surface of the inwards concave regular quadrangular frustum and the left side surface (; the distance between the highest point of the intersecting line of the upper side surface (19) of the concave regular quadrangular frustum and the cylinder of the head part (1) of the device is 0.5-2 mm from the top of the head part (1) of the device; the axes of the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively vertical to the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20) and respectively pass through the middle points of the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20); the pressure measuring middle hole (6) is circular, the diameter of the pressure measuring middle hole is 0.1-1 mm, and the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are all circular, have the diameter of 0.05-0.8 mm and are smaller than the diameter of the pressure measuring middle hole (6);

furthermore, a square shallow groove with the side length of 0.5-3 mm is formed in the rear side surface (15) opposite to the top surface (16) of the concave regular quadrangular frustum and the depth of the groove is 0.3-1 mm, and a square deep groove with the side length of 0.3-2 mm and smaller than the shallow groove is formed in the groove and is concentric with the shallow groove and the depth of the groove is the same; the size of the heat insulation fixing piece (4) is the same as that of the shallow groove and the heat insulation fixing piece is arranged in the shallow groove; the temperature sensor (3) is a film thermal resistor or a film thermocouple, the size of the temperature sensor is the same as that of the heat insulation fixing piece (4), the temperature sensor is adhered to the surface of the heat insulation fixing piece (4), and a temperature sensor cable (12) is led out of the tail part of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;

further, the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 3-10 mm, and the axis of the device supporting rod (2) is overlapped with the axis of the cylinder of the device head (1);

furthermore, a device for accurately measuring the temperature rise efficiency of the compressor stage is calibrated, and incoming flow flows through the measuring device in a standard wind tunnel with known incoming flow Mach number and speed; recording the pressure of 5 pressure measuring holes on the surface of the windward side of the measuring device and the temperature of a temperature sensor on the leeward side of the measuring device; and determining calibration curves of total pressure coefficients, static pressure coefficients, deflection angle coefficients and total temperature recovery coefficients under different Mach numbers and different deflection angles and pitch angles through data processing according to the data obtained by calibration. The yaw angle coefficient, pitch angle coefficient, total pressure coefficient, static pressure coefficient and temperature recovery coefficient are defined as follows:

wherein, C_pyAs coefficient of deflection angle, C_ppIs the coefficient of pitch angle, C_ptIs the total pressure coefficient, C_psIs a static pressure coefficient, C_TFor recovering temperatureCounting, wherein the total pressure, the static pressure, the total temperature and the static temperature of the incoming flow in the calibration wind tunnel are respectively P_t、P_s、T_tAnd T_sThe pressure values measured by the middle hole, the left hole, the right hole, the upper hole and the lower hole of the five-hole pressure probe are respectively P₁、P₂、P₃、P₄And P₅The temperature value measured by the temperature sensor is T_pTherefore, calibration curves of the total pressure coefficient, the static pressure coefficient, the deflection angle coefficient, the pitch angle coefficient and the total temperature recovery coefficient of the device under different Mach numbers and different deflection angles and pitch angles can be obtained;

the measuring device comprises two measuring point position arrangement schemes during measurement, wherein the first measured gas compressor progressive and outlet measuring point arrangement scheme comprises the following steps:

for an inlet, selecting a section of a pressure-measured compressor stage inlet, which is 0.05-1.5 times of blade chord length away from the front edge of a rotor blade, as an inlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the cascade pitch of a single rotor blade of a compressor stage; on an inlet test section, selecting 7-11 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; the method comprises the following steps that 5-7 measuring positions are arranged in the circumferential direction, different circumferential measuring positions are concentrated in a fan-shaped measuring area of the grid pitch of a rotor blade grid and are dense at positions close to blades, and parameters in a measured trail are guaranteed to be sparse in the middle of a channel;

for an outlet, selecting a section which is 0.05-1 times of the chord length of the blade from the tail edge of the stator blade after the outlet of the tested compressor stage as an outlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the grid pitch of the single stator blade grid of the compressor stage; on the outlet test section, selecting 9-15 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; 7-13 measurement positions are circumferentially arranged, different circumferential measurement positions are concentrated in a fan-shaped measurement area of the grid pitch of the stator blade grid, the measurement positions are dense at positions close to the blades, and parameters in a measured trail are guaranteed to be sparse in the middle of a channel;

the second arrangement scheme of the tested air compressor grading and outlet measuring points is as follows:

for an inlet, selecting a section which is 0.05 to 1.5 times of the chord length of the blade in front of the inlet of a tested compressor stage and is away from the front edge of the rotor blade as an inlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the cascade pitch of the single rotor blade of the compressor stage; selecting 7-11 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; the method comprises the following steps of arranging 5-7 measuring positions in the circumferential direction, simultaneously using a plurality of measuring devices which are respectively distributed in fan-shaped measuring areas with a plurality of rotor blade grid pitches, enabling at most one circumferential measuring position to exist in each measuring fan-shaped measuring area, and enabling the circumferential measuring positions in different fan-shaped measuring areas to be dense at positions close to blades after rotating the circumferential measuring positions in the different fan-shaped measuring areas to the same fan-shaped measuring area by using the axis of a gas compressor as a rotation center by an integral multiple of the angle corresponding to a single rotor blade grid pitch, so that the parameters in a trail can be measured by the circumferential measuring positions, and the circumferential measuring positions are sparse at the middle part of a;

for the outlet, selecting a section which is 0.05 to 1 time of blade chord length away from the tail edge of the stator blade after the outlet of the tested compressor stage as an outlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the grid pitch of the single stator blade grid of the compressor stage; selecting 9-15 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; 7-13 measuring positions are circumferentially arranged, a plurality of measuring devices are used at the same time, and are respectively distributed in a plurality of fan-shaped measuring areas with stator blade cascade grid distances, so that at most one circumferential measuring position exists in each measuring fan-shaped measuring area, and when the circumferential measuring positions in the different fan-shaped measuring areas are rotated to the same fan-shaped measuring area by an integral multiple of the angle corresponding to a single stator blade cascade grid distance by taking the axis of a gas compressor as a rotation center, the density of the positions close to blades can still be ensured, so that the parameters in a trail can be measured, and the density of the positions in a channel is sparse;

further, carrying out test measurement, namely arranging the device at the initial position of the progressive and outlet measuring section of the gas compressor, and adjusting the turbine to enter a test state; measuring and recording the pressure of the 5 pressure measuring holes, and measuring and recording the temperature of the temperature sensor; driving the measuring device to enter the next radial position by using the displacement mechanism and repeating the process until all measuring point positions are reached;

furthermore, according to data of 5 pressure measuring holes and data of a temperature sensor, a deflection angle coefficient and a pitch angle coefficient are obtained, and then a calibrated coefficient curve is combined to obtain the deflection angle, the pitch angle, the total pressure, the static pressure and the Mach number of each measuring point through interpolation. And the incoming flow velocity is obtained by the following formula:

c²＝γRT_s

P_s＝ρRT_s

wherein gamma is the adiabatic index of the flow field, Ma is the mach number of the flow field, v is the flow field velocity, c is the local acoustic velocity of the flow field, R is the gas constant, and ρ is the density;

further, the total temperature of the progressive inlet of the air compressor is obtained by using a mass weighting method

Inlet total pressure

Total outlet temperature

Total pressure at the outlet

Parameters, the formula is as follows:

wherein the content of the first and second substances,

is a mass-weighted average of the measured cross-sectional parameters, v_iIs the velocity value of point i, A_iIs the area value, alpha, corresponding to the i measurement point_iIs the deflection angle, beta, of point i_iIs the pitch angle of the i measuring point, X_iThe parameter value of the i measuring points, i is the number of the measuring points, and j is the total number of the measuring points;

further, the temperature rise efficiency of the tested gas compressor stage is calculated by the following formula:

Figure DEST_PATH_GDA00026551337100000510

according to the device for accurately measuring the temperature rise efficiency of the compressor stage, the measuring device can obtain a calibration curve after being calibrated through the calibration wind tunnel; in actual measurement, based on data measured by five pressure measuring holes and a temperature sensor, total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, pitch angle, speed and density parameters of a measured three-dimensional steady-state flow field can be simultaneously obtained through data processing according to a calibration coefficient curve and a formula obtained by calibrating a calibration wind tunnel, the service life of the temperature sensor is prolonged, the insensitive angle range of airflow is widened, and the measurement spatial resolution and the measurement precision are improved; the measuring method can accurately measure the temperature rise efficiency of the single stage of the multistage compressor by optimizing the measuring point layout and the quality weighting averaging method.

The invention has the beneficial effects that:

the beneficial effects are that:

according to the device for accurately measuring the temperature rise efficiency of the compressor stage, the total temperature, the total pressure, the static temperature, the static pressure, the Mach number, the deflection angle, the pitch angle, the speed and the density of the interstage flow field of the compressor can be measured by using a single device, the structure is compact, the size is small, the interference on the measured flow field is effectively reduced, and the test precision is improved; meanwhile, the test operation is simplified, and the test cost is reduced.

The beneficial effects are that:

the device for accurately measuring the stage temperature rise efficiency of the compressor is back to the main stream and is positioned in the low-speed separation area of the leeward side of the head of the device, so that the scouring of air flow to the temperature sensor is firstly reduced, meanwhile, the influence of oil drops, dust and the like mixed in the air flow on the temperature sensor is reduced, and the service life of the temperature sensor is effectively prolonged; secondly, the strength requirement on the temperature sensor is low, and the size of the temperature sensor can be small, so that the size of the head of the device is effectively reduced, and the spatial resolution is improved; thirdly, the range of the separation low-speed area is large, and the heat exchange between the airflow and the temperature sensor is effectively enhanced by the vortex in the separation area, so that the temperature recovery coefficient is high and stable in a large deflection angle range during measurement;

the beneficial effects are three:

according to the device for accurately measuring the temperature rise efficiency of the compressor stage, the measuring method eliminates the system error caused by arithmetic mean and area mean in the conventional method through a quality weighting method, improves the measuring precision of the compressor stage, the total outlet temperature and the total pressure, and further can accurately measure the temperature rise efficiency of the compressor stage.

The beneficial effects are four:

according to the device for accurately measuring the temperature rise efficiency of the compressor stage, the measuring method breaks through the limitation that the conventional method can only measure the overall efficiency of the multi-stage compressor by a new measuring point distribution mode, and the measurement of the single-stage temperature rise efficiency of the multi-stage compressor is realized.

Drawings

Fig. 1 is a schematic structural diagram of an apparatus according to a first embodiment of the present invention.

Fig. 2 is a rear view of fig. 1.

Fig. 3 is a left side view of fig. 1.

Fig. 4 is a partial cross-sectional view of fig. 3.

Fig. 5 is a view from direction a of fig. 1.

Fig. 6 is a view from direction B of fig. 2.

Fig. 7 is a partial view of fig. 1.

Wherein: 1-device head, 2-device support rod, 3-temperature sensor, 4-adiabatic insulation fixing piece, 5-temperature sensor cable leading-out channel, 6-pressure measuring middle hole, 7-pressure measuring left hole, 8-pressure measuring right hole, 9-pressure measuring upper hole, 10-pressure measuring lower hole, 11-pressure guiding pipe channel, 12-temperature sensor cable, 13-pressure guiding pipe, 14-front side, 15-back side, 16-concave regular quadrangular frustum top surface, 17-concave regular quadrangular frustum left side surface, 18-concave regular quadrangular frustum right side surface, 19-concave regular quadrangular frustum upper side surface and 20-concave regular quadrangular frustum lower side surface.

Fig. 8 is an installation diagram of the first embodiment of the present invention.

Wherein: 1-hub, 2-casing, 3-compressor stator, 4-measuring device of the invention for measuring parameters of stage inlet, 5-measured compressor stage rotor, 6-measured compressor stage stator, 7-measuring device of the invention for measuring parameters of stage outlet.

FIG. 9 is a schematic diagram of a compressor stage inlet test point arrangement according to an embodiment of the present invention.

Wherein: 1-casing, 2-radial measurement position, 3-circumferential measurement position, 4-hub.

FIG. 10 is a schematic diagram of a compressor stage outlet test point arrangement according to an embodiment of the present invention.

Fig. 11 is a schematic structural diagram of an apparatus according to a second embodiment of the present invention.

Fig. 12 is a rear view of fig. 11.

Fig. 13 is a left side view of fig. 11.

Fig. 14 is a partial cross-sectional view of fig. 13.

Fig. 15 is a view from direction a of fig. 11.

Fig. 16 is a view from direction B of fig. 12.

Fig. 17 is a partial view of fig. 11.

Fig. 18 is an installation diagram of the second embodiment of the present invention.

Wherein: 1-hub, 2-casing, 3-compressor stator, 4-inventive measuring device for measuring parameters of stage inlet, 5-measured compressor stage rotor, 6-measured compressor stage stator, 7-inventive measuring device for measuring parameters of stage outlet, 8-compressor rotor.

FIG. 19 is a schematic view of the arrangement of inlet test points of a compressor stage according to the second embodiment of the present invention.

FIG. 20 is a schematic diagram of the arrangement of compressor stage outlet test points according to the second embodiment of the present invention.

Fig. 21 is a schematic structural diagram of an apparatus according to a third embodiment of the present invention.

Fig. 22 is a rear view of fig. 21.

Fig. 23 is a left side view of fig. 21.

Fig. 24 is a partial cross-sectional view of fig. 23.

Fig. 25 is a view from direction a of fig. 21.

Fig. 26 is a view from direction B of fig. 22.

Fig. 27 is a partial view of fig. 21.

Fig. 28 is an installation diagram of the third embodiment of the present invention.

FIG. 29 is a schematic diagram of the arrangement of inlet test points of three compressor stages according to an embodiment of the present invention.

Wherein: 1-compressor stage rotor blade, 2-casing, 3-casing, 4-measuring actual circumferential position, 5-measuring circumferential position after rotating to a sector measuring area, and 6-measuring radial position.

FIG. 30 is a schematic diagram of the arrangement of the outlet test points of the three compressor stages according to the embodiment of the invention.

Wherein: 1-compressor stage stator blade, 2-casing, 3-casing, 4-measuring actual circumferential position, 5-measuring circumferential position after rotating to a sector measuring area, and 6-measuring radial position.

Detailed Description

The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, will make the advantages and features of the invention easier to understand by those skilled in the art, and thus will clearly and clearly define the scope of the invention.

The first embodiment is as follows:

for a low-pressure compressor of an aircraft engine, the size is relatively large, the incoming flow speed is high, and impurities such as dust, water drops and the like can be contained. The head and the support rod of the device should have larger sizes to ensure the strength and rigidity, the pressure measuring hole should have a larger aperture to avoid the blockage of impurities, and more measuring positions should be selected to improve the overall accuracy of the test, so the following embodiments (fig. 1-10 are schematic diagrams of an embodiment) can be adopted:

the utility model provides a device for accurate measurement compressor level temperature rise efficiency, by device head (1), device branch (2), temperature sensor (3), adiabatic insulating mounting (4), temperature sensor cable draw-out passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), pressure measurement upper punch (9), pressure measurement lower punch (10), pressure measurement pipe passageway (11), temperature sensor cable (12), pressure measurement pipe (13), leading flank (14), trailing flank (15), the positive four prismatic table top surface of indent (16), the positive four prismatic table left surface of indent (17), the positive four prismatic table right flank of indent (18), the positive four prismatic table upper flank of indent (19), the positive four prismatic table downside of indent (20) are constituteed, its characterized in that: the device head (1) is a cylinder, the windward side is a front side (14), an inwards concave regular quadrangular frustum top surface (16), an inwards concave regular quadrangular frustum left side surface (17), an inwards concave regular quadrangular frustum right side surface (18), an inwards concave regular quadrangular frustum upper side surface (19) and an inwards concave regular quadrangular frustum lower side surface (20), the leeward side is a rear side surface (15), the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively arranged on the inwards concave regular quadrangular frustum top surface (16), the inwards concave regular quadrangular frustum left side surface (17), the inwards concave regular quadrangular frustum right side surface (18), the inwards concave regular quadrangular frustum upper side surface (19) and the inwards concave regular quadrangular frustum lower side surface (20), and the leeward side of the device head opposite to the pressure measuring middle hole (6) is provided with a temperature sensor (3);

furthermore, the diameter of a cylinder of the head part (1) of the device is 5 mm, the height of the cylinder is 20 mm, 5 circular pressure leading pipe channels (11) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other are axially arranged in the head part of the device, the 5 circular pressure leading pipe channels (11) are respectively communicated with a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure measuring upper hole (9) and a pressure measuring lower hole (10) and are respectively communicated with five pressure leading pipes (13) which are packaged at the connecting part of the head part of the device (1) and the device supporting rod (2), and the pressure leading pipes (13) are led out of the tail part of the device supporting rod (2) through the pressure leading pipe channels (11;

furthermore, the front side surface (14) of the head part (1) of the device is provided with an inwards concave regular quadrangular frustum, the upper edge of the top surface (16) of the inwards concave regular quadrangular frustum is vertical to the cylindrical axis of the head part (1) of the device, the length of the top surface is 2 mm, the distance between the top surface (16) of the inwards concave regular quadrangular frustum and the cylindrical axis of the head part (1) of the device is 1 mm, the cylindrical surface of the head part (1) of the bottom surface of the inwards concave regular quadrangular frustum is tangent, and the included angle between the bottom surface of the inwards concave regular quadrangular frustum and the left side surface (17); the highest point of the intersecting line of the upper side surface (19) of the concave regular quadrangular frustum and the cylinder of the head part (1) of the device is 1 mm away from the top of the head part (1) of the device; the axes of the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively vertical to the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20) and respectively pass through the middle points of the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20); the pressure measuring middle hole (6) is circular, the diameter of the pressure measuring middle hole is 0.8 mm, and the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are all circular, and the diameter of the pressure measuring middle hole is 0.4 mm;

furthermore, a square shallow groove with the side length of 2 mm is formed in the rear side surface (15) opposite to the top surface (16) of the concave regular quadrangular frustum and the depth of the groove is 1 mm, and a square deep groove with the side length of 1 mm is formed in the groove and is concentric with the shallow groove and the depth of the groove is the same; the size of the heat insulation fixing piece (4) is the same as that of the shallow groove and the heat insulation fixing piece is arranged in the shallow groove; the temperature sensor (3) is a film thermal resistor, the size of the temperature sensor is the same as that of the heat insulation fixing piece (4), the temperature sensor is adhered to the surface of the heat insulation fixing piece (4), and a temperature sensor cable (12) is led out of the tail part of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;

further, the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 6 mm, and the axis of the device supporting rod (2) is overlapped with the axis of the cylinder of the device head (1);

wherein, C_pyAs coefficient of deflection angle, C_ppIs the coefficient of pitch angle, C_ptIs the total pressure coefficient, C_psIs a static pressure coefficient, C_TFor the temperature recovery coefficient, the total pressure, the static pressure, the total temperature and the static temperature of the incoming flow in the wind tunnel are calibrated to be P respectively_t、P_s、T_tAnd T_sThe pressure values measured by the middle hole, the left hole, the right hole, the upper hole and the lower hole of the five-hole pressure probe are respectively P₁、P₂、P₃、P₄And P₅The temperature value measured by the temperature sensor is T_pTherefore, calibration curves of the total pressure coefficient, the static pressure coefficient, the deflection angle coefficient, the pitch angle coefficient and the total temperature recovery coefficient of the device under different Mach numbers and different deflection angles and pitch angles can be obtained;

the arrangement scheme of the tested air compressor stage and the outlet measuring point is as follows:

for an inlet, selecting a section of a blade chord length which is 0.1 time of the front edge of a rotor blade of the inlet of a tested compressor stage as an inlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the cascade pitch of a single rotor blade of the compressor stage; on an inlet test section, selecting 9 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; 7 measurement positions are circumferentially arranged, different circumferential measurement positions are concentrated in a fan-shaped measurement area of the grid pitch of the rotor blade grid, the measurement positions are dense at positions close to blades, parameters in a measured wake are guaranteed, and the measurement positions are sparse in the middle of a channel;

for the outlet, selecting a section of a blade chord length which is 0.1 time of the blade chord length from the tail edge of the stator blade after the outlet of the tested compressor stage as an outlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the grid pitch of a single stator blade grid of the compressor stage; on the outlet test section, 13 radial positions are selected as radial measuring points and are densely arranged at the positions close to the hub and the casing, so that the parameters in the boundary layer are ensured to be measured; 9 measurement positions are circumferentially arranged, different circumferential measurement positions are concentrated in a fan-shaped measurement area of the grid pitch of the stator blade grid and are dense at positions close to the blades, so that the measured parameters in the trail are ensured to be sparse in the middle of a channel;

further, carrying out test measurement, namely measuring the initial positions of the cross sections of the progressive and outlet measuring devices of the air compressor, and adjusting the aero-engine to enter a test state; measuring and recording the pressure of the 5 pressure measuring holes, and measuring and recording the temperature of the temperature sensor; driving the measuring device to enter the next radial position by using the displacement mechanism and repeating the process until all measuring point positions are reached;

c²＝γRT_s

P_s＝ρRT_s

Inlet total pressure

Total outlet temperature

Total pressure at the outlet

Parameters, the formula is as follows:

wherein the content of the first and second substances,

is a mass-weighted average of the measured cross-sectional parameters, v_iIs the velocity value of point i, A_iIs the area value, alpha, corresponding to the i measurement point_iIs the deflection angle, beta, of point i_iIs the pitch angle of the i measuring point, X_iIs the parameter value of the i measuring points, i is the number of measuring points, j is the total number of measuring pointsCounting;

Figure DEST_PATH_GDA00026551337100001010

example two:

for a high-pressure compressor of an aircraft engine, the incoming flow speed is relatively low, but the axial and radial sizes are small, and the flow is complex. The head and the support rod of the device should be selected to have smaller dimensions to reduce blockage as much as possible, the pressure measuring hole should be selected to have smaller aperture to improve spatial resolution, and less measuring point positions are selected due to spatial limitation, so that the following embodiments can be adopted (fig. 11-20 are schematic diagrams of the second embodiment):

furthermore, the diameter of a cylinder of the head part (1) of the device is 2 mm, the height of the cylinder is 5 mm, 5 circular pressure leading pipe channels (11) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other are axially arranged in the head part of the device, the 5 circular pressure leading pipe channels (11) are respectively communicated with a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure measuring upper hole (9) and a pressure measuring lower hole (10) and are respectively communicated with five pressure leading pipes (13) which are packaged at the connecting part of the head part of the device (1) and the device supporting rod (2), and the pressure leading pipes (13) are led out of the tail part of the device supporting rod (2) through the pressure leading pipe channels (11;

furthermore, the front side surface (14) of the head part (1) of the device is provided with an inwards concave regular quadrangular frustum, the upper edge of the top surface (16) of the inwards concave regular quadrangular frustum is vertical to the cylindrical axis of the head part (1) of the device, the length is 0.6 mm, the distance between the top surface (16) of the inwards concave regular quadrangular frustum and the cylindrical axis of the head part (1) of the device is 0.5 mm, and is not more than 0.25 times of the diameter of the cylinder of the head part (1), the cylindrical surface of the head part (1) of the bottom surface of the inwards concave regular quadrangular frustum is tangent, and the included angle between the bottom surface of the inwards concave regular quadrangular frustum and the left side; the distance between the highest point of the intersecting line of the upper side surface (19) of the concave regular quadrangular frustum and the cylinder of the head part (1) of the device is 0.5 mm from the top of the head part (1) of the device; the axes of the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively vertical to the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20) and respectively pass through the middle points of the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20); the pressure measuring middle hole (6) is circular, the diameter of the pressure measuring middle hole is 0.3 mm, and the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are all circular, and the diameter of the pressure measuring middle hole is 0.2 mm;

furthermore, a square shallow groove with the side length of 0.5 mm and the depth of 0.3 mm is formed in the rear side surface (15) opposite to the top surface (16) of the concave regular quadrangular frustum, and a square deep groove with the side length of 0.3 mm is formed in the groove and is concentric with the shallow groove and has the same depth; the size of the heat insulation fixing piece (4) is the same as that of the shallow groove and the heat insulation fixing piece is arranged in the shallow groove; the temperature sensor (3) is a film thermal resistor, the size of the temperature sensor is the same as that of the heat insulation fixing piece (4), the temperature sensor is adhered to the surface of the heat insulation fixing piece (4), and a temperature sensor cable (12) is led out of the tail part of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;

further, the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 3 mm, and the axis of the device supporting rod (2) is overlapped with the axis of the cylinder of the device head (1);

for an inlet, selecting a section of a blade chord length which is 0.08 times of the blade chord length of the front edge of a rotor blade of the inlet of a tested compressor stage as an inlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the cascade pitch of a single rotor blade of the compressor stage; on an inlet test section, selecting 7 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; the method comprises the following steps that 5 measuring positions are circumferentially arranged, different circumferential measuring positions are concentrated in a fan-shaped measuring area of the grid pitch of the rotor blade grid and are dense at positions close to blades, and parameters in a measured trail are guaranteed to be sparse in the middle of a channel;

for the outlet, selecting a section of a blade chord length which is 0.08 times of the blade chord length of the tail edge of the stator blade after the outlet of the tested compressor stage as an outlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the grid pitch of a single stator blade grid of the compressor stage; on the outlet test section, selecting 9 radial positions as radial measuring points, and densely arranging the radial measuring points at the positions close to the hub and the casing to ensure that parameters in the boundary layer are measured; 7 measurement positions are circumferentially arranged, different circumferential measurement positions are concentrated in a fan-shaped measurement area of the grid pitch of the stator blade grid, the measurement positions are dense at positions close to blades, parameters in a measured trail are guaranteed, and the measurement positions are sparse in the middle of a channel;

c²＝γRT_s

P_s＝ρRT_s

Inlet total pressure

Total outlet temperature

Total pressure at the outlet

Parameters, the formula is as follows:

wherein the content of the first and second substances,

example three:

for the high-pressure compressor of the aircraft engine in the second embodiment, the measurement space is narrow, and a second measuring point arrangement scheme can be used for measurement (fig. 21-30 are schematic diagrams of the second embodiment):

for an inlet, selecting a section of a blade chord length which is 0.08 times of the blade chord length of the front edge of a rotor blade of the inlet of a tested compressor stage as an inlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the cascade pitch of a single rotor blade of the compressor stage; selecting 7 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; the method is characterized in that 6 measuring positions are circumferentially arranged, a plurality of measuring devices are simultaneously used and are respectively distributed in fan-shaped measuring areas with 6 rotor blade grid pitches, and when the circumferential measuring positions in the different fan-shaped measuring areas rotate to the same fan-shaped measuring area by an integral multiple of the corresponding angle of the single rotor blade grid pitch by taking the axis of a gas compressor as a rotation center, the circumferential measuring positions can still be ensured to be dense at the positions close to blades, so that the circumferential measuring positions can measure parameters in a trail and have a sparse principle in the middle of a channel;

for the outlet, selecting a section which is 0.05 to 1 time of blade chord length away from the tail edge of the stator blade after the outlet of the tested compressor stage as an outlet test section, and dividing the test section into a plurality of fan-shaped measurement areas according to the grid pitch of the single stator blade grid of the compressor stage; selecting 11 radial positions as radial measuring points, wherein the radial measuring points are densely arranged at positions close to a hub and a casing, and parameters in a boundary layer are guaranteed to be measured; the method is characterized in that 8 measuring positions are circumferentially arranged, a plurality of measuring devices are simultaneously used and are respectively distributed in fan-shaped measuring areas with 8 stator blade grid distances, and when the circumferential measuring positions in the different fan-shaped measuring areas are rotated to the same fan-shaped measuring area by an angle corresponding to an integral multiple of a single stator blade grid distance by taking the axis of a gas compressor as a rotation center, the circumferential measuring positions close to blades can be still ensured to be dense, so that the circumferential measuring positions can measure parameters in a trail and are sparse in the middle of a channel;

c²＝γRT_s

P_s＝ρRT_s

Inlet total pressure

Total outlet temperature

Total pressure at the outlet

Parameters, the formula is as follows:

wherein the content of the first and second substances,

Figure DEST_PATH_GDA00026551337100001510

Claims

1. the utility model provides a device for accurate measurement compressor level temperature rise efficiency, by device head (1), device branch (2), temperature sensor (3), adiabatic insulating mounting (4), temperature sensor cable draw-out passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), pressure measurement upper punch (9), pressure measurement lower punch (10), pressure measurement pipe passageway (11), temperature sensor cable (12), pressure measurement pipe (13), leading flank (14), trailing flank (15), the positive four prismatic table top surface of indent (16), the positive four prismatic table left surface of indent (17), the positive four prismatic table right flank of indent (18), the positive four prismatic table upper flank of indent (19), the positive four prismatic table downside of indent (20) are constituteed, its characterized in that: the device head (1) is a cylinder, the windward side is a front side (14), an inwards concave regular quadrangular frustum top surface (16), an inwards concave regular quadrangular frustum left side surface (17), an inwards concave regular quadrangular frustum right side surface (18), an inwards concave regular quadrangular frustum upper side surface (19) and an inwards concave regular quadrangular frustum lower side surface (20), the leeward side is a rear side surface (15), the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively arranged on the inwards concave regular quadrangular frustum top surface (16), the inwards concave regular quadrangular frustum left side surface (17), the inwards concave regular quadrangular frustum right side surface (18), the inwards concave regular quadrangular frustum upper side surface (19) and the inwards concave regular quadrangular frustum lower side surface (20), and the rear side surface (15) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);

the diameter of a cylinder of the head part (1) of the device is 2-8 mm, the height of the cylinder is 5-30 mm, 5 circular pressure leading pipe channels (11) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other are axially arranged in the head part of the device, the 5 circular pressure leading pipe channels (11) are respectively communicated with a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure measuring upper hole (9) and a pressure measuring lower hole (10) and are respectively communicated with five pressure leading pipes (13) which are packaged at the connecting part of the head part of the device (1) and the device supporting rod (2), and the tail parts of the device supporting rod (2) are led out of the pressure leading pipe channels (11) in the device supporting rod (;

the front side surface (14) of the head part (1) of the device is provided with an inwards concave regular quadrangular frustum, the upper edge of the top surface (16) of the inwards concave regular quadrangular frustum is vertical to the cylindrical axis of the head part (1) of the device, the length of the inwards concave regular quadrangular frustum is 0.5-3 mm, the distance between the top surface (16) of the inwards concave regular quadrangular frustum and the cylindrical axis of the head part (1) of the device is 0.5-2 mm, and is not more than 0.25 times of the diameter of the cylinder of the head part (1), the bottom surface of the inwards concave regular quadrangular frustum is tangent to the cylindrical surface of the head part (1) of the device, and the included angle between the bottom surface of the inwards concave; the distance between the highest point of the intersecting line of the upper side surface (19) of the concave regular quadrangular frustum and the cylinder of the head part (1) of the device is 0.5-2 mm from the top of the head part (1) of the device; the axes of the pressure measuring middle hole (6), the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are respectively vertical to the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20) and respectively pass through the middle points of the concave square frustum top surface (16), the concave square frustum left side surface (17), the concave square frustum right side surface (18), the concave square frustum upper side surface (19) and the concave square frustum lower side surface (20); the pressure measuring middle hole (6) is circular, the diameter of the pressure measuring middle hole is 0.1-1 mm, and the pressure measuring left hole (7), the pressure measuring right hole (8), the pressure measuring upper hole (9) and the pressure measuring lower hole (10) are all circular, have the diameter of 0.05-0.8 mm and are smaller than the diameter of the pressure measuring middle hole (6);

a square shallow groove with the side length of 0.5-3 mm is formed in the rear side surface (15) opposite to the top surface (16) of the concave regular quadrangular frustum and the depth of the groove is 0.3-1 mm, and a square deep groove with the side length of 0.3-2 mm and smaller than the shallow groove is formed in the groove and is concentric with the shallow groove and the depth of the groove is the same; the size of the heat insulation fixing piece (4) is the same as that of the shallow groove and the heat insulation fixing piece is arranged in the shallow groove; the temperature sensor (3) is a film thermal resistor or a film thermocouple, the size of the temperature sensor is the same as that of the heat insulation fixing piece (4), the temperature sensor is adhered to the surface of the heat insulation fixing piece (4), and a temperature sensor cable (12) is led out of the tail part of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;

the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 3-10 mm, and the axis of the device supporting rod (2) coincides with the axis of a cylinder of the head (1) of the device.