High-temperature-resistant airflow pipeline structure

Abstract

The utility model discloses a high-temperature-resistant airflow pipeline structure which comprises a shell on the outermost layer, a main cylinder on the middle layer and a lining on the innermost layer. A cooling layer is also arranged between the shell and the main cylinder; a thermal insulation layer is further arranged between the main cylinder body and the lining, the lining is provided with a communicating hole, and main airflow in the pipeline is communicated with the thermal insulation layer. The communicating holes are formed in the lining, the thermal insulation layer is communicated with main airflow, heat of the main barrel is taken away through the cooling layer, the gas temperature of the thermal insulation layer is reduced to a small extent, heat transfer is also conducted on the wall face of the lining, and therefore the heat of the lining is taken away; due to blocking of the lining, gas in the thermal insulation layer does not circulate, and the temperature of the gas does not affect main gas flow; the structure not only ensures that the temperature and components of the main airflow center layer are not changed, but also reduces the temperature resistance level of the main cylinder body to a normal state, so that the main cylinder body can resist the temperature of 2000 DEG C.

Description

TECHNICAL FIELD

[0001] The utility model relates to a high temperature airflow conveying technical field more particularly, relate to a kind of high-temperature airflow pipeline structure. BACKGROUND

[0002] In the field of aero-engine, in order to detect the parameters such as combustion efficiency, residual gas coefficient, combustion temperature and exhaust pollutant of aero-engine, gas analysis test needs to be done. Gas analysis is to introduce gas into analysis measuring instrument for composition analysis by pipeline. Due to the continuous increase of thrust-to-weight ratio of aero-engine, the outlet temperature of combustion chamber is also continuously increased, which has exceeded 2000℃, which exceeds the bearing range of most high-temperature pipelines.

[0003] Invention patent CN102229360B discloses an aviation kerosene high-temperature gas flow generating device, which replaces the traditional first-stage pre-combustion mode with a high-efficiency stainless steel electric heater array at the inlet of the combustion chamber, and two variable-frequency pumps are used to independently supply oil to the two flame tubes for gas generation. The high-temperature pipeline adopts a water-cooled internal insulation structure, which includes an inner layer composed of ceramic lining, a middle layer made of high-temperature powdery material, and an outer layer composed of water-cooled stainless steel pipeline. The ceramic lining is prone to thermal stress under high temperature, and the material is prone to deformation and cracking when the temperature changes rapidly. Invention patent CN113006964B discloses an S-bend converging-diverging nozzle with a cooling structure, belonging to the field of aero-engine. It includes a converging section, a diverging section, and a film cooling structure. The inlet of the first nozzle section of the converging section is the air inlet, and the outlet of the second nozzle section is the nozzle throat. The inlet of the diverging section is sleeved around the periphery of the nozzle throat, with an overlapping portion in the axial direction, forming an annular gap between them as a film cooling slot. The film cooling structure includes an annular cooling gas passage, a cooling passage support plate, a film cooling hole, and a film cooling slot. The cooling passage outer wall is fixed to the periphery of the nozzle along the circumference through the cooling passage support plate, forming an annular cooling gas passage. The film cooling hole is opened on the outer wall of the converging section. The cooling gas flows into the nozzle through the film cooling hole and the film cooling slot, and covers the inner wall of the high-temperature nozzle. This scheme introduces cooling gas into the interior of the aero-engine exhaust nozzle and covers the inner wall of the nozzle for cooling effect. This way of introducing other cooling gas will interfere with the composition analysis data of the gas analysis test, so the pipeline of this scheme is not suitable for gas delivery for gas analysis test. UTILITY MODEL CONTENT

[0004] The utility model discloses in order to solve the problem that pipeline cannot bear 2000℃ high temperature in the prior art, proposes a kind of high-temperature airflow pipeline structure.

[0005] The utility model discloses the following technical scheme realizes:

[0006] A kind of high-temperature resistant airflow pipe structure, including outermost shell, intermediate layer main cylinder, innermost lining;Cooling layer is further provided between the shell and main cylinder;Heat insulation layer is further provided between the main cylinder and lining, and the lining is opened with communication hole, and the main airflow in pipeline is communicated with heat insulation layer.

[0007] Further, the heat insulation layer thickness is 5-10mm.

[0008] Further, the heat insulation layer is provided with support rib, and surrounds the main cylinder.

[0009] Further, the communication hole divides the cross section of lining into four equal parts, and the width of communication hole is 2-5mm.

[0010] Further, the shell is stainless steel shell, and the thickness is 3-6mm.

[0011] Further, the main cylinder is stainless steel cylinder.

[0012] Further, the lining is high-temperature resistant alloy material, and the thickness is 8-12mm, and the thickness of high-temperature resistant coating on the lining is 1-5mm.

[0013] Further, the cooling layer is circulated with water.

[0014] Further, the cooling layer thickness is 8-10mm.

[0015] Further, the surface of lining contacted with main gas is coated with high-temperature resistant coating.

[0016] Compared with prior art, the beneficial effects of the utility model are:

[0017] The utility model discloses a communication hole is set up on the lining, and the heat insulation layer is communicated with the main airflow, and then the heat of main cylinder is taken away through cooling layer, so that the gas temperature of heat insulation layer is reduced slightly, and the heat of lining is taken away through heat transfer of lining wall surface;Due to the blocking of lining, the temperature of heat insulation layer gas does not affect the main airflow;The structure guarantees that the temperature of main airflow center layer does not change, and reduces the temperature resistance grade of lining to conventional high temperature (≤1300 DEG C) state, and reduces the temperature resistance grade of main cylinder to normal state, so that it can resist 2000 DEG C temperature;Meanwhile, the composition of main airflow is not changed, so that the aviation engine gas analysis test is more accurate. BRIEF DESCRIPTION OF DRAWINGS

[0018] Fig. 1 It is a kind of high-temperature resistant airflow pipe airflow direction cross section structure schematic view;

[0019] Fig. 2 It is a kind of high-temperature resistant airflow pipe circumferential direction cross section structure schematic view;

[0020] Fig. 3 Schematic diagram of the cross section of the inner liner in the direction of the gas flow.

[0021] Wherein: 1, shell; 2, cooling layer; 3, main cylinder; 4, temperature insulation layer; 5, inner liner; 6, main gas flow channel; 7, rib plate; 8, high-temperature-resistant coating; 9, communication hole. DETAILED DESCRIPTION

[0022] To clearly illustrate the technical features of the present scheme, the following through specific implementation, and combining its drawings, the utility model is described in detail. In the following description, a lot of specific details are set forth in order to fully understand the present application, however, the present application can also be implemented in other ways different from the description herein, therefore, the protection scope of the present application is not limited by the specific embodiments disclosed below. In addition, in the description of the present application, it is understood that the terms "center", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features limited by "first", "second" can be explicitly or implicitly included one or more features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited. In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected, or it can be communicated; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication or interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances. In the present application, unless otherwise explicitly specified and limited, the first feature is "on" or "under" the second feature, which can be the direct contact of the first and second features, or the indirect contact of the first and second features through an intermediate medium. In the description of the present application, the description of the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0023] Embodiment 1

[0024] Please refer to Figs. 1 to 3The embodiment provides a high-temperature-resistant gas flow pipeline structure, which comprises an outermost shell 1, an intermediate main cylinder 3, and an innermost inner liner 5; a cooling layer 2 is further arranged between the shell 1 and the main cylinder 3; a temperature insulation layer 4 is further arranged between the main cylinder 3 and the inner liner 5; and the inner liner 5 is provided with a communication hole 9, so that the main gas in a main gas flow channel 6 is communicated with the temperature insulation layer 4.

[0025] In the embodiment, the shell 1 is a stainless steel shell with a thickness of 3 mm, and the main cylinder 3 is a stainless steel cylinder with a thickness calculated according to the pressure resistance of the pipeline under the normal temperature state; the shell 1 and the main cylinder 3 mainly play a supporting role; and the cross-sectional shape of the shell 1, the main cylinder 3 and the inner liner 5 is circular. Since the aviation engine gas has a certain pressure during the gas analysis test, the circular pipeline can effectively bear the pressure and is not easy to deform or break.

[0026] Cooling water is circulated in the cooling layer 2, the cooling layer channel has a width of 5-10 mm, the thickness of the cooling layer in the embodiment is 5 mm, the cooling water is connected with an external circulation system, the external circulation system can be connected with an ice-water machine, the cooling water is subjected to cooling treatment and then pressurization treatment, so that heat exchange is more efficient, the cooling water absorbs and removes the temperature of the main cylinder 3, thereby reducing the temperature of the main cylinder 3, and the temperature is prevented from being transmitted to the shell 1, so that the temperature of the shell 1 is maintained at a level close to the ambient temperature, and the stable operation of other equipment is prevented from being affected by high-temperature emission.

[0027] The temperature insulation layer 4 is located between the main cylinder 3 and the inner liner 5, the high-temperature-resistant rib plate 7 is welded around the circumferential section of the main cylinder 3, the rib plate 7 is arranged in the pipeline of the main cylinder 3 at intervals, one group of rib plates 7 is arranged at intervals of about 300 mm, so that a gap is formed between the main cylinder 3 and the inner liner 5, the temperature insulation layer is formed, and the inner liner 5 is supported, so that the overall structural strength and impact resistance of the pipeline are improved.

[0028] The inner liner 5 is made of a high-temperature-resistant alloy material and has a thickness of about 4-8 mm, and the thickness of the inner liner 5 in the embodiment is 4 mm; the thickness of the temperature insulation layer 4 is controlled in the range of 5-10 mm, and the thickness of the temperature insulation layer 4 in the embodiment is 5 mm.

[0029] The working principle of the structure is as follows: the super-high-temperature aero-engine gas enters the main gas flow channel and contacts the inner lining 5 made of high-temperature-resistant alloy material, the gas entering the main gas flow channel passes through the communication holes 9 on the inner lining 5 into the temperature insulation layer 4, so that the gas entering the temperature insulation layer 4 becomes temperature insulation gas, the temperature insulation gas further performs heat transfer with the main cylinder 3, the cooling layer 2 outside the main cylinder 3 performs cooling water circulation cooling, the heat of the main cylinder 3 is taken away, the temperature of the outermost shell 1 is maintained at a level close to the ambient temperature, and the gas temperature of the temperature insulation layer 4 is reduced by a small amplitude, heat transfer is performed on the wall surface of the inner lining 5, so that the heat of the inner lining 5 is taken away, and the temperature of the temperature insulation layer gas is not affected by the main gas flow due to the blocking of the inner lining 5; the structure ensures that the temperature of the central layer gas does not change, and reduces the temperature resistance grade of the main cylinder 3 to normal, and reduces the temperature resistance grade of the inner lining 5 to a conventional high temperature (≤1300℃) state, which makes the pipeline material selection range wider and the cost greatly reduced; and the temperature and composition data collected in the gas analysis test are more accurate, which also provides a guarantee for stable operation of the overall equipment.

[0030] Embodiment 2

[0031] Please refer to Figs. 1 to 3 The embodiment provides a high-temperature-resistant gas flow pipeline structure, which comprises an outermost shell 1, a middle-layer main cylinder 3 and an innermost inner lining 5; a cooling layer 2 is further arranged between the shell 1 and the main cylinder 3; a temperature insulation layer 4 is further arranged between the main cylinder 3 and the inner lining 5, and the inner lining 5 is provided with communication holes 9 to communicate the main gas in a main gas flow channel 6 with the temperature insulation layer 4.

[0032] In the embodiment, the shell 1 is a stainless steel shell with a thickness of 4 mm, and the main cylinder 3 is a stainless steel cylinder, the thickness of the main cylinder is calculated according to the pressure resistance of the pipeline under normal temperature, and the shell 1 and the main cylinder 3 mainly play a supporting role; the cross-sectional shape of the shell 1, the main cylinder 3 and the inner lining 5 is circular, because there is a certain pressure of aero-engine gas during the gas analysis test, the circular pipeline can effectively withstand the pressure and is not easy to deform or break.

[0033] Cooling water is circulated in the cooling layer 2, the width of the cooling layer 2 is 12 mm, the cooling water is connected with an external circulation system, the external circulation system can be connected with an ice water machine, the cooling water is first cooled and then pressurized, so that the heat exchange is more efficient, the cooling water absorbs and takes away the temperature of the main cylinder 3, thereby reducing the temperature of the main cylinder 3, and preventing the temperature from being transmitted to the shell 1, so that the temperature of the shell 1 is maintained at a level close to the ambient temperature, and the stable operation of other equipment is avoided from being affected by high-temperature emission.

[0034] The temperature insulation layer 4 is located between the main cylinder 3 and the inner liner 5, and is formed by welding high-temperature-resistant rib plates 7 around the circumferential section of the main cylinder 3, the rib plates 7 being arranged at intervals in the pipeline of the main cylinder 3, about 300 mm for a group, so that a gap is formed between the main cylinder 3 and the inner liner 5, forming a temperature insulation layer, and forming a supporting effect on the inner liner 5, improving the overall structural strength and impact resistance of the pipeline.

[0035] The inner liner 5 is made of high-temperature-resistant alloy material, and has a thickness of about 4-8 mm, and in this embodiment, the thickness is 8 mm; the thickness of the temperature insulation layer 4 is controlled in the range of 5-10 mm, and in this embodiment, the thickness is 10 mm.

[0036] Further, the surface of the inner liner 5 in contact with the main gas is coated with a high-temperature-resistant coating 8, which can provide better protection and heat insulation effect, thereby improving the service life of the inner liner 5.

[0037] The working principle of the structure is as follows: the ultra-high-temperature aviation engine gas enters the main gas flow channel and contacts the inner liner 5 made of high-temperature-resistant alloy material, and at the same time, the high-temperature-resistant coating on the surface of the inner liner 5 forms a protection for the inner liner 5, so that the high-temperature-resistant performance of the inner liner 5 is enhanced; at the same time that the gas enters the main gas flow channel, it enters the temperature insulation layer 4 through the communication hole 9 on the inner liner 5, so that the gas entering the temperature insulation layer 4 becomes temperature insulation gas, the temperature insulation gas is in heat transfer with the main cylinder 3, the outer cooling layer 2 of the main cylinder 3 is arranged to circulate cooling water for cooling, the heat of the main cylinder 3 is taken away, the temperature of the outermost shell 1 is maintained at a level close to the ambient temperature, and the temperature of the gas in the temperature insulation layer 4 is reduced slightly, and the heat is transferred to the wall surface of the inner liner 5, so that the heat of the inner liner 5 is taken away, and due to the blocking of the inner liner 5, the temperature of the temperature insulation layer gas does not affect the main gas flow; this structure not only ensures that the temperature of the central layer gas does not change, but also reduces the temperature resistance grade of the main cylinder 3 to normal, and the temperature resistance grade of the inner liner 5 is reduced to the conventional high temperature (≤1300℃) state, which makes the selection range of the pipeline material wider and the cost greatly reduced; and the temperature and composition data collected in the gas analysis test are more accurate, which also provides a guarantee for the stable operation of the overall equipment.

[0038] Embodiment 3

[0039] Please refer to Figs. 1 to 3 , the embodiment provides a high-temperature-resistant gas flow pipeline structure, which comprises an outermost shell 1, a middle layer main cylinder 3, and an innermost inner liner 5; the shell 1 and the main cylinder 3 are further provided with a cooling layer 2; the surface of the inner liner 5 in contact with the main gas is coated with a high-temperature-resistant coating 8; the main cylinder 3 and the inner liner 5 are further provided with a temperature insulation layer 4, and the inner liner 5 is provided with a communication hole 9 to communicate the main gas in the main gas flow channel 6 with the temperature insulation layer 4.

[0040] In the embodiment, the shell 1 is a stainless steel shell with a thickness of 5 mm, and the main cylinder 3 is a stainless steel cylinder with a thickness calculated according to the pressure resistance of the pipeline under normal temperature. The shell 1 and the main cylinder 3 mainly play a supporting role. The cross-sectional shape of the shell 1, the main cylinder 3 and the inner liner 5 is circular. Since the aviation engine gas has a certain pressure during the gas analysis test, the circular pipeline can effectively withstand these pressures and is not prone to deformation or rupture.

[0041] The cooling layer 2 is filled with cooling water, and the thickness of the cooling layer 2 is 9 mm. The cooling water is connected to an external circulation system, which can be connected to an ice water machine. The cooling water is first cooled and then pressurized to make heat exchange more efficient. The cooling water absorbs and carries away the temperature of the main cylinder 3, thereby reducing the temperature of the main cylinder 3, and at the same time, isolating the temperature from being transmitted to the shell 1, so that the temperature of the shell 1 is maintained at a level close to the ambient temperature, avoiding the influence of high temperature emission on the stable operation of other equipment.

[0042] The temperature insulation layer 4 is located between the main cylinder 3 and the inner liner 5. By welding high-temperature-resistant rib plates 7 around the circumference of the cross section of the main cylinder 3, the rib plates 7 are arranged at intervals in the pipeline of the main cylinder 3, about 300 mm for a group, so that a gap is formed between the main cylinder 3 and the inner liner 5 to form a temperature insulation layer, and the inner liner 5 is supported to improve the overall structural strength and impact resistance of the pipeline.

[0043] The inner liner 5 is made of high-temperature-resistant alloy material with a thickness of about 4-8 mm, and the thickness of the inner liner 5 in the embodiment is 6 mm. The thickness of the temperature insulation layer 4 is controlled in the range of 5-10 mm, and the thickness of the temperature insulation layer 4 in the embodiment is 8 mm.

[0044] Further, the communication hole 9 divides the cross section of the inner liner 5 into four equal parts, and the width of the communication hole 9 is 3.5 mm. The communication hole 9 is distributed on the circumferential surface of the inner liner 5, and the gas in the main gas flow channel is introduced into the temperature insulation layer 4 through the communication hole 9.

[0045] The working principle of the structure is: the super-high-temperature aero-engine gas enters the main gas flow channel and contacts the inner lining 5 made of high-temperature-resistant alloy material, and the high-temperature-resistant coating on the surface of the inner lining 5 protects the inner lining 5, so that the high-temperature-resistant performance of the inner lining 5 is enhanced; at the same time, the gas enters the temperature insulation layer 4 through the communication holes 9 on the inner lining 5, so that the gas entering the temperature insulation layer 4 becomes temperature insulation gas, the temperature insulation gas is in heat transfer with the main cylinder 3, the cooling layer 2 outside the main cylinder 3 is provided to circulate cooling water for cooling, the heat of the main cylinder 3 is taken away, so that the temperature of the outermost shell 1 is maintained at a level close to the ambient temperature, and the temperature of the gas in the temperature insulation layer 4 is reduced slightly, and heat transfer is also performed on the wall surface of the inner lining 5, so that the heat of the inner lining 5 is taken away, and due to the blocking of the inner lining 5, the temperature of the temperature insulation layer gas does not affect the main gas flow; the structure ensures that the temperature of the central layer gas does not change, and reduces the temperature resistance grade of the main cylinder 3 to normal, and reduces the temperature resistance grade of the inner lining 5 to the conventional high temperature (≤1300℃) state, which makes the pipeline material selection range wider, and the cost is greatly reduced; and the temperature and composition data collected in the gas analysis test are more accurate, which also provides protection for stable operation of the overall equipment.

[0046] In a certain gas analysis experiment, the main gas flow temperature is 2100℃, and when the high-temperature-resistant gas flow pipeline structure in the embodiment is used for conveying, the main gas flow temperature is measured as: 2100℃ (center), 2050℃ (wall); the temperature of the temperature insulation layer gas is 1260℃, and the temperature of the outer cylinder is 40℃, which achieves good high-temperature-resistant effect and has little effect on the main gas flow.

[0047] It is obvious for those skilled in the art that the present application is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, the scope of the present application is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application, and any reference signs in the claims should not be regarded as limiting the claims.

Claims

1. A high temperature resistant gas flow duct structure, characterized by: The shell comprises an outermost shell, a middle layer main cylinder, and an innermost inner liner; a cooling layer is arranged between the shell and the main cylinder; a temperature insulation layer is arranged between the main cylinder and the inner liner; and the inner liner is provided with a communication hole for connecting the main gas flow in the pipeline with the temperature insulation layer.

2. A high temperature resistant airflow duct structure according to claim 1, wherein: The thickness of the temperature insulation layer is 5-10 mm.

3. A high temperature resistant airflow duct structure according to claim 1, wherein: The temperature insulation layer is provided with a support rib plate and surrounds the main cylinder.

4. A high temperature resistant airflow duct structure according to claim 1, wherein: The communication hole divides the cross section of the inner liner into four equal parts, and the width of the communication hole is 2-5 mm.

5. A high temperature resistant airflow duct structure according to claim 1, wherein: The shell is a stainless steel shell with a thickness of 3-6 mm.

6. A high temperature resistant airflow duct structure according to claim 1, wherein: The main cylinder is a stainless steel cylinder.

7. A high temperature resistant airflow duct structure according to claim 1, wherein: The inner liner is made of a high-temperature-resistant alloy material with a thickness of 8-12 mm.

8. A high temperature resistant airflow duct structure according to claim 1, wherein: Circulating water is circulated in the cooling layer.

9. A high temperature resistant airflow duct structure according to claim 1, wherein: The thickness of the cooling layer is 8-10 mm.

10. A high temperature resistant airflow duct structure according to claim 1, wherein: The surface of the inner liner in contact with the main gas is coated with a high-temperature-resistant coating.

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