Ventilation and heat dissipation device of nacelle core cabin, control method and aero-engine

Abstract

The invention provides a ventilation and heat dissipation device of a nacelle core cabin, a control method and an aero-engine. The ventilation and heat dissipation device of the nacelle core cabin comprises an air entraining main pipe, a multi-way valve, a plurality of air entraining branch pipes and a heat insulation flow guide structure. One end of the air entraining main pipe introduces outer culvert air from the outside of the core cabin cover and communicates with the multiple air entraining branch pipes through the multi-way valve. The multi-way valve is used for controlling connection and disconnection of the air entraining main pipe and the air entraining branch pipes. The heat insulation flow guide structure wraps the engine case, on one hand, heat radiation of the engine case to the interior of the core cabin space can be isolated, and on the other hand, the heat insulation flow guide structure is further provided with a first flow channel arranged around the gas compressor section, a second flow channel arranged around the combustion chamber section and a third flow channel arranged around the turbine section. And the first flow channel, the second flow channel and the third flow channel communicate with the multi-way valve through air entraining branch pipes correspondingly, and therefore the air compressor section, the combustion chamber section and the turbine section are cooled in a targeted mode through introduced outer culvert air.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to a ventilation and heat dissipation device of a nacelle core cabin, a control method and an aeroengine. Background Art

[0002] The core compartment of an aircraft engine nacelle is equipped with a large number of complex pipes, cables and accessories. Combustible materials such as fuel and lubricating oil, as well as ignition sources such as cables and high-temperature hot surfaces may exist in this area. The spatial structure and flow and heat environment are extremely complex.

[0003] At present, in order to cool down and dissipate the heat of the core cabin of the nacelle and protect the cables and accessories arranged in the core cabin, a method of cooling down and dissipating the heat of the core cabin in the nacelle by introducing external bypass gas has been proposed. However, the current heat dissipation device has technical problems such as unsatisfactory cooling effect and low cooling gas utilization efficiency. Summary of the invention

[0004] The purpose of the present invention is to provide a ventilation and heat dissipation device, a control method and an aircraft engine for a nacelle core cabin, which can improve the technical problems of unsatisfactory cooling effect of the core cabin and low cooling air utilization efficiency in the prior art.

[0005] The embodiments of the present invention can be implemented in the following ways:

[0006] A ventilation and heat dissipation device for a nacelle core cabin, wherein a core cabin space and an exhaust gap connecting the core cabin space with an external atmospheric environment are formed between an engine casing and a core cabin cover in the core cabin; the ventilation and heat dissipation device for the nacelle core cabin is arranged in the core cabin space and comprises:

[0007] An air bleed main pipe, one end of which passes through the core nacelle cover to introduce external air;

[0008] A multi-way valve and a plurality of air bleed branches connected to the multi-way valve, the air bleed main pipe and the multi-way valve, and the multi-way valve is used to control the opening and closing of the air bleed main pipe and the air bleed branch pipe; and

[0009] A heat-insulating flow-guiding structure, wherein the heat-insulating flow-guiding structure wraps the engine casing; the heat-insulating flow-guiding structure has a compressor section, a combustion chamber section and a turbine section which are connected in sequence, and the heat-insulating flow-guiding structure has a first flow channel arranged around the compressor section, a second flow channel arranged around the combustion chamber section and a third flow channel arranged around the turbine section, the first flow channel, the second flow channel and the third flow channel are respectively connected to the multi-way valve through an air bleed branch pipe, and the first flow channel, the second flow channel and the third flow channel are respectively used to spray the outer bypass gas into the core cabin space.

[0010] Optionally, the heat insulation and flow guiding structure includes a heat insulation plate and a plurality of outlet pipes, the heat insulation plate is arranged to wrap the engine casing, and the heat insulation plate has the compressor section, the combustion chamber section and the turbine section; the plurality of outlet pipes are arranged in the compressor section to form the first flow channel, the plurality of outlet pipes are arranged in the combustion chamber section to form the second flow channel, and the plurality of outlet pipes are arranged in the turbine section to form the third flow channel.

[0011] Optionally, the outlet pipe is detachably connected to the heat insulation board.

[0012] Optionally, the outlet pipe is provided with a plurality of inner holes and a plurality of outer holes, wherein the plurality of inner holes are arranged toward the heat insulation board to spray the outer duct gas toward the heat insulation board; and the plurality of outer holes are arranged toward the core cabin space to spray the outer duct gas toward the core cabin space.

[0013] Optionally, along the circumferential direction of the outlet pipe, the inner holes and the outer holes are alternately arranged.

[0014] Optionally, the outlet pipe forming the first flow channel is a first outlet pipe, and the central angle between adjacent inner holes and outer holes on the first outlet pipe is α, 10°≤α≤20°; and / or,

[0015] The outlet pipe forming the second flow channel is a second outlet pipe, and the central angle corresponding to the adjacent inner holes and outer holes on the second outlet pipe is β, 10°≤β≤20°;

[0016] The outlet pipe forming the third flow channel is the third outlet pipe, and the central angle corresponding to the adjacent inner holes and the external measurement and control holes on the third outlet pipe is γ, and 10°≤γ≤20°.

[0017] Optionally, the outlet pipe is an annular shape connected end to end, and the first flow channel, the second flow channel and the third flow channel are respectively formed by a plurality of outlet pipes arranged side by side; an end of the air induction branch pipe away from the multi-way valve is provided with an air collecting shell, the air collecting shell has an air collecting cavity and a plurality of air outlet notches connected to the air collecting cavity, and the air collecting cavity is connected to the air induction branch pipe; the outlet pipe is clamped to the air outlet notch, and is connected to the air collecting cavity through the air outlet notch;

[0018] Among them, the air collecting shell connected to the first flow channel is the first air collecting shell, and the number of air outlet notches on the first air collecting shell is consistent with the number of outlet pipes of the first flow channel; the air collecting shell connected to the second flow channel is the second air collecting shell, and the number of air outlet notches on the second air collecting shell is consistent with the number of outlet pipes of the second flow channel; the air collecting shell connected to the third flow channel is the third air collecting shell, and the number of air outlet notches on the third air collecting shell is consistent with the number of outlet pipes of the third flow channel.

[0019] Optionally, the number of outlet pipes included in the first flow channel is a, 4≤a≤6; and / or,

[0020] The number of outlet pipes included in the second flow channel is b, 2≤b≤3; and / or,

[0021] A portion of the outlet pipes included in the third flow channel are high-pressure turbine outlet pipes, and another portion are low-pressure turbine outlet pipes; the number of high-pressure turbine outlet pipes is c, 2≤c≤3; the number of low-pressure turbine outlet pipes is d, 4≤d≤6.

[0022] Optionally, the communication position between the heat insulation and flow guiding structure and the air bleed branch pipe is located at the top of the engine casing.

[0023] An aircraft engine comprises a core cabin and the ventilation and heat dissipation device of the nacelle core cabin.

[0024] A heat dissipation control method for a nacelle core cabin is used to control a multi-way valve in a ventilation and heat dissipation device of the nacelle core cabin. The heat dissipation control method for the nacelle core cabin comprises:

[0025] Detect and determine whether the temperatures of the compressor part, the combustion chamber part, and the turbine part exceed the threshold value;

[0026] When the temperature of the compressor part exceeds a threshold value, controlling the multi-way valve to connect the bleed air branch pipe connected to the first flow channel with the bleed air main pipe;

[0027] When the temperature of the combustion chamber portion exceeds a threshold value, controlling the multi-way valve to connect the bleed air branch pipe connected to the second flow channel with the bleed air main pipe;

[0028] When the temperature of the turbine part exceeds a threshold value, the multi-way valve is controlled to connect the bleed air branch pipe connected to the third flow passage with the bleed air main pipe.

[0029] The beneficial effects of the ventilation and heat dissipation device, control method and aircraft engine of the nacelle core cabin provided by the embodiments of the present invention include:

[0030] An embodiment of the present invention provides a ventilation and heat dissipation device for a nacelle core cabin, which is arranged in the core cabin space and includes a bleed air main pipe, a multi-way valve, a plurality of bleed air branch pipes, and a heat insulation and flow guiding structure. One end of the bleed air main pipe introduces external air from outside the core cabin cover and is connected to the plurality of bleed air branch pipes through the multi-way valve. The multi-way valve is used to control the opening and closing of the bleed air main pipe and the bleed air branch pipe. The heat-insulating and flow-guiding structure wraps the engine casing. On the one hand, it can isolate the heat radiation of the engine casing to the core engine compartment space and protect the cables and accessories arranged in the core engine compartment. On the other hand, it also has a first flow channel arranged around the compressor section, a second flow channel arranged around the combustion chamber section and a third flow channel arranged around the turbine section. The first flow channel, the second flow channel and the third flow channel are respectively connected to the multi-way valve through an air bleed branch pipe, so that the compressor section, the combustion chamber section and the turbine section are cooled in a targeted manner by the introduced external bypass gas, thereby strengthening the convective heat exchange near the engine casing and the core engine compartment space, and ensuring the temperature safety of the cables and accessories in the core engine compartment. At the same time, the external bypass gas entering the core engine compartment space can be discharged from the exhaust gap, thereby strengthening ventilation and reducing the accumulation of combustible vapors.

[0031] An embodiment of the present invention also provides an aircraft engine, which includes the above-mentioned ventilation and heat dissipation device of the nacelle core cabin, and thus can also isolate the heat radiation of the engine casing to the core cabin space, and through the introduced external gas, the compressor section, the combustion chamber section and the turbine section are cooled in a targeted manner, thereby strengthening the convective heat exchange near the engine casing and the core cabin space, ensuring the temperature safety of the cables and accessories in the core cabin, and at the same time, the external gas entering the core cabin space can be discharged from the exhaust gap, thereby enhancing ventilation and reducing the accumulation of combustible vapors.

[0032] The embodiment of the present invention also provides a heat dissipation control method for a nacelle core compartment, which is used to control a multi-way valve in a ventilation and heat dissipation device of the nacelle core compartment, the method comprising: detecting and judging whether the temperatures of the compressor section, the combustion chamber section and the turbine section are respectively within the threshold value; when the temperature of the compressor section exceeds the threshold value, the multi-way valve is controlled to connect the bleed air branch pipe connected to the first flow channel with the bleed air main pipe; when the temperature of the combustion chamber section exceeds the threshold value, the multi-way valve is controlled to connect the bleed air branch pipe connected to the second flow channel with the bleed air main pipe; when the temperature of the turbine section exceeds the threshold value, the multi-way valve is controlled to connect the bleed air branch pipe connected to the third flow channel with the bleed air main pipe. By independently controlling the cooling of the compressor section, the combustion chamber section and the turbine section, cooling can be achieved more accurately and the utilization rate of the bypass gas can be improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0034] Figure 1 It shows a schematic diagram of the overall structure of a ventilation and heat dissipation device of a nacelle core cabin provided according to one aspect of the present invention;

[0035] Figure 2 It shows a schematic diagram of the longitudinal cross-section structure of a ventilation and heat dissipation device of a nacelle core cabin provided according to one aspect of the present invention;

[0036] Figure 3 A schematic structural diagram showing a part of the structure of a ventilation and heat dissipation device of a nacelle core cabin provided according to one aspect of the present invention;

[0037] Figure 4 A schematic structural diagram of a heat insulation and flow guiding structure in a ventilation and heat dissipation device of a nacelle core cabin provided according to one aspect of the present invention is shown;

[0038] Figure 5 A schematic structural diagram of a first outlet pipe provided according to one aspect of the present invention is shown;

[0039] Figure 6 A partial structural schematic diagram of an outlet pipe provided according to one aspect of the present invention is shown;

[0040] Figure 7 A flow chart of a heat dissipation control method for a nacelle core compartment provided according to one aspect of the present invention is shown.

[0041] Reference numerals:

[0042] 100-ventilation and heat dissipation device of the nacelle core cabin; 111-engine casing; 112-core cabin cover; 113-core cabin space; 114-exhaust gap; 121-air bleed main pipe; 122-multi-way valve; 123-air bleed branch pipe; 124-controller; 125-gas collecting shell; 1251-first gas collecting shell; 1252-second gas collecting shell; 1253-third gas collecting shell; 126-gas collecting cavity ; 127-air outlet notch; 130-heat insulation guide structure; 131-heat insulation board; 132-outlet pipe; 1321-first outlet pipe; 1322-second outlet pipe; 1323-third outlet pipe; 1324-high-pressure turbine outlet pipe; 1325-low-pressure turbine outlet pipe; 133-compressor section; 134-combustion chamber section; 135-turbine section; 136-inlet; 137-inner hole; 138-outer hole DETAILED DESCRIPTION

[0043] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0044] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0045] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0046] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] Figure 1 The overall structural diagram of the ventilation and heat dissipation device 100 of the nacelle core cabin provided in this embodiment is shown. Figure 2 FIG. 1 shows a schematic diagram of the longitudinal cross-sectional structure of a ventilation and heat dissipation device 100 for a nacelle core cabin provided in this embodiment. Figure 3 The schematic diagram of the structure of part of the ventilation and heat dissipation device 100 of the nacelle core cabin provided in this embodiment is shown. Figure 4 The schematic diagram of the structure of the heat insulation and flow guiding structure 130 in the ventilation and heat dissipation device 100 of the nacelle core cabin provided in this embodiment is shown. Figure 1-Figure 4 This embodiment provides a ventilation and heat dissipation device 100 for a nacelle core cabin, and accordingly, also provides an aircraft engine (not shown). The aircraft engine includes the ventilation and heat dissipation device 100 for a nacelle core cabin, and also includes other components of the aircraft engine such as a compressor, a combustion chamber, etc.

[0048] The ventilation and heat dissipation device 100 of the nacelle core cabin includes an air bleed main pipe 121, a multi-way valve 122, a plurality of air bleed branches 123, and a heat insulation and flow guiding structure 130. One end of the air bleed main pipe 121 introduces the external air from the outside of the core cabin cover 112, and is connected to the plurality of air bleed branches 123 through the multi-way valve 122. The multi-way valve 122 is used to control the opening and closing of the air bleed main pipe 121 and the air bleed branch pipe 123. The heat-insulating and flow-guiding structure 130 wraps the engine casing 111. On the one hand, it can isolate the heat radiation of the engine casing 111 to the core engine compartment space 113, and protect the cables and accessories arranged in the core engine compartment. On the other hand, it also has a first flow channel arranged around the compressor section 133, a second flow channel arranged around the combustion chamber section 134, and a third flow channel arranged around the turbine section 135. The first flow channel, the second flow channel and the third flow channel are respectively connected to the multi-way valve 122 through an air bleed branch pipe 123, so that the compressor section 133, the combustion chamber section 134 and the turbine section 135 are cooled and lowered in a targeted manner by the introduced external gas, thereby strengthening the convective heat exchange near the engine casing 111 and the core engine compartment space 113, and ensuring the temperature safety of the cables and accessories in the core engine compartment. At the same time, the external gas entering the core engine compartment space 113 can be discharged from the exhaust gap 114, thereby strengthening ventilation and reducing the accumulation of combustible vapors.

[0049] Specifically, the core cabin space 113 is formed by the engine casing 111 and the core cabin cover 112 in the core cabin, and the exhaust gap 114 that connects the core cabin space 113 with the outside atmosphere is formed, and the exhaust gap 114 is located at the tail of the core cabin space 113. The engine casing 111 and the core cabin cover 112 are both annular structures, so the core cabin space 113 formed between the engine casing 111 and the core cabin cover 112 is also annular. The ventilation and heat dissipation device 100 of the nacelle core cabin is arranged in the core cabin space 113, and the external air is introduced into the core cabin space 113 through the ventilation and heat dissipation device 100 of the nacelle core cabin, so as to cool the core cabin space 113, and the gas entering the core cabin space 113 is discharged from the exhaust gap 114 to the outside atmosphere, thereby taking away the heat, and at the same time, the ventilation in the core cabin space 113 is strengthened to avoid the accumulation of combustible vapor entering the core cabin space 113.

[0050] like Figure 4As shown, in this embodiment, the heat insulation and flow guiding structure 130 includes a heat insulation board 131 and a plurality of outflow pipes 132. The heat insulation board 131 wraps the engine casing 111, thereby isolating the heat radiation of the engine casing 111 and reducing the heat conducted from the engine casing 111 to the core cabin space 113. Specifically, the heat insulation board 131 is an annular (or tubular) component that wraps the surface of the engine casing 111, covers the outer peripheral wall of the engine casing 111, and adopts a high-temperature resistant metal material with low thermal conductivity, such as high-temperature alloy 625, so as to prevent the engine casing 111 from radiating heat into the core cabin space 113. The heat shield 131 has a compressor section 133, a combustion chamber section 134 and a turbine section 135. Accordingly, the compressor section 133 is a portion of the heat shield 131 located at the same axial position as the compressor, the combustion chamber section 134 is a portion of the heat shield 131 located at the same axial position as the combustion chamber, and the turbine section 135 is a portion of the heat shield 131 located at the same axial position as the turbine. In the description of this embodiment, "axial" means Figure 2 In the L direction shown, the exhaust gap 114 is located on the side of the turbine section 135 axially away from the combustion chamber section 134 .

[0051] Some of the multiple outlet pipes 132 are arranged outside the compressor section 133 to form a first flow channel. In other words, the compressor section 133 is located at the location of the first flow channel. Some of the multiple outlet pipes 132 are arranged outside the combustion chamber section 134 to form a second flow channel. In other words, the combustion chamber section 134 is located at the location of the second flow channel. Some of the multiple outlet pipes 132 are arranged outside the turbine section 135 to form a third flow channel. In other words, the turbine section 135 is located at the location of the third flow channel. Further, since the turbine includes a high-pressure turbine and a low-pressure turbine, in this embodiment, some of the multiple outlet pipes 132 that form the third flow channel are the high-pressure turbine outlet pipe 1324, and the other part are the low-pressure turbine outlet pipe 1325.

[0052] In this embodiment, the outlet pipe 132 is an annular tubular member connected end to end, and a plurality of outlet pipes 132 forming a first flow channel are arranged side by side in the compressor section 133 at intervals along the axial direction, a plurality of outlet pipes 132 forming a second flow channel are arranged side by side in the combustion chamber section 134 at intervals along the axial direction, and a plurality of outlet pipes 132 forming a third flow channel are arranged side by side in the compressor section 133 at intervals along the axial direction. Optionally, the outlet pipe 132 is detachably connected to the heat insulation board 131, so that the outlet pipe 132 can be replaced, repaired, etc. without removing the heat insulation board. Specifically, a groove or the like that is engaged with the outlet pipe 132 can be provided on the heat insulation board 131, so that the outlet pipe 132 can be detachably fixed to the heat insulation board 131.

[0053] The first flow channel, the second flow channel and the third flow channel are respectively formed by a plurality of outlet pipes 132 arranged side by side. Specifically, the outlet pipe 132 forming the first flow channel is a first outlet pipe 1321, the outlet pipe 132 forming the second flow channel is a second outlet pipe 1322, and the outlet pipe 132 forming the third flow channel is a third outlet pipe 1323, and the third outlet pipe 1323 includes a high-pressure turbine outlet pipe 1324 and a low-pressure turbine outlet pipe 1325.

[0054] Optionally, the number of outlet pipes 132 included in the first flow channel, that is, the number of first outlet pipes 1321, is a, 4≤a≤6. The number of outlet pipes 132 included in the second flow channel, that is, the number of second outlet pipes 1322, is b, 2≤b≤3. The number of high-pressure turbine outlet pipes 1324 is c, 2≤c≤3. The number of low-pressure turbine outlet pipes 1325 is d, 4≤d≤6. Specifically, the number of outlet pipes 132 in the first flow channel can be set to 4, 5 or 6. The number of outlet pipes 132 in the second flow channel can be set to 2 or 3. The number of high-pressure turbine outlet pipes 1324 can be set to 2 or 3. The number of low-pressure turbine outlet pipes 1325 can be set to 4, 5 or 6.

[0055] An air collecting housing 125 is provided at one end of the air bleed branch pipe 123 away from the multi-way valve 122. The air collecting housing 125 has an air collecting cavity 126 and a plurality of air outlet notches 127 connected to the air collecting cavity 126. The air collecting cavity 126 is connected to the air bleed branch pipe 123. The outlet pipe 132 is clamped to the air outlet notch 127 and is connected to the air collecting cavity 126 through the air outlet notch 127. In this embodiment, there are three air bleed branch pipes 123, and an air collecting housing 125 is provided at the air outlet end (i.e., the end away from the multi-way valve 122) of each air bleed branch pipe 123. Accordingly, there are three air collecting housings 125, and the multi-way valve 122 is a four-way valve.

[0056] Among them, the air collecting shell 125 connected to the first flow channel is the first air collecting shell 1251, and the number of air outlet notches 127 on the first air collecting shell 1251 is consistent with the number of first outlet pipes 1321. In this way, through the first air collecting shell 1251 and the air inlet branch pipe 123 connected to the first air collecting shell 1251, multiple first outlet pipes 1321 are connected to the multi-way valve 122, and the multi-way valve 122 is used to transport the external gas to the first outlet pipe 1321 to cool the compressor section 133. The air collecting shell 125 connected to the second flow channel is the second air collecting shell 1252. The number of air outlet notches 127 on the second air collecting shell 1252 is consistent with the number of second outlet pipes 1322. In this way, through the second air collecting shell 1252 and the air inlet branch pipe 123 connected to the second air collecting shell 1252, multiple second outlet pipes 1322 are connected to the multi-way valve 122, and the external gas is transported to the second outlet pipes 1322 through the multi-way valve 122 to cool the combustion chamber section 134. The air collecting shell 125 connected to the third flow channel is the third air collecting shell 1253. The number of air outlet notches 127 on the third air collecting shell 1253 is consistent with the number of third outlet pipes 1323. In this way, through the third air collecting shell 1253 and the air inlet branch pipe 123 connected to the third air collecting shell 1253, multiple third outlet pipes 1323 are connected to the multi-way valve 122, and the external bypass gas is transported to the third outlet pipe 1323 through the multi-way valve 122 to cool the turbine section 135.

[0057] In this embodiment, the communication structure between the first outlet pipe 1321 and the first gas collecting housing 1251, the communication structure between the second outlet pipe 1322 and the second gas collecting housing 1252, and the communication structure between the third outlet pipe 1323 and the third gas collecting housing 1253 are consistent, so the communication structure between the outlet pipe 132 and the gas collecting housing 125 is described here by taking the structure of the first outlet pipe 1321 as an example. Specifically, Figure 5 The structure of the first outlet pipe 1321 provided in this embodiment is shown. Figure 1-Figure 5 The outlet pipe 132 is provided with an air inlet 136, which is arranged along the circumferential direction of the outlet pipe 132 ( Figure 5 The air inlet 136 is a square opening extending in the R direction as shown in FIG. 1 , and the extension length of the air inlet 136 is substantially consistent with the width of the air collecting housing 125. It should be noted that in the description of this embodiment, the "circumferential direction of the outlet flow pipe 132" refers to the circumferential direction of the annular structure formed by the flow pipe 132, in other words, it can also be regarded as the circumferential direction of the heat insulation board 131.

[0058] The gas collecting housing 125 is a generally square housing, and a gas collecting cavity 126 is formed inside the housing. The bottom of the gas collecting housing 125 is open to form an opening, and a gas outlet notch 127 of the gas collecting housing 125 is arranged at the opening of the gas collecting housing 125, and is a semicircular notch that penetrates the gas collecting housing 125 along the width direction of the gas collecting housing 125. When the outlet pipe 132 is clamped at the gas outlet notch 127, the air inlet 136 of the outlet pipe 132 faces the gas outlet notch 127, so as to communicate with the gas collecting cavity 126 through the gas outlet notch 127. When the multi-way valve 122 connects the bleed air branch pipe 123 at the first air collecting shell 1251 with the bleed air main pipe 121, the by-gas introduced into the bleed air main pipe 121 passes through the multi-way valve 122 and the bleed air branch pipe 123 and enters the air collecting cavity 126 of the first air collecting shell 1251, and then enters the first outlet pipe 1321 through the air inlet 136 of the first outlet pipe 1321, and then sprays the by-gas into the core cabin space 113 through the first outlet pipe 1321, thereby cooling the compressor section 133.

[0059] Further, since the third outlet pipe 1323 includes a high-pressure turbine outlet pipe 1324 and a low-pressure turbine outlet pipe 1325, the third air collecting housing 1253 includes a first housing portion for mounting the high-pressure turbine outlet pipe 1324 and a second housing portion for mounting the low-pressure turbine outlet section, and the first housing portion and the second housing portion together form the air collecting cavity 126 of the third air collecting housing 1253. Therefore, in this embodiment, the high-pressure turbine outlet pipe 1324 and the low-pressure turbine outlet pipe 1325 simultaneously eject or stop ejecting the outer gas under the control of the multi-way valve 122. Optionally, the first housing portion is bent relative to the second housing portion, and the first housing portion and the second housing portion are distributed at an obtuse angle.

[0060] Figure 6 This is a partial structural diagram of the outlet pipe 132 provided in this embodiment. Figure 1-Figure 6In this embodiment, the outlet pipe 132 is provided with a plurality of inner holes 137 and a plurality of outer holes 138, and the plurality of inner holes 137 and the plurality of outer holes 138 can eject the outer duct gas outward. The plurality of inner holes 137 are arranged toward the heat shield 131, so that the outer duct gas ejected from the inner holes 137 is ejected toward the heat shield 131, and the vicinity of the engine casing 111 is cooled down. The plurality of outer holes 138 are arranged toward the core cabin space 113, so as to eject the outer duct gas toward the core cabin space, thereby cooling the cables and accessories arranged in the core cabin space 113. It should be noted that, although in the present embodiment, the outlet pipe 132 is arranged in the core cabin space 113, the external gas ejected from the inner hole 137 and the outer hole 138 eventually enters the core cabin space 113, the ejection direction of the inner hole 137 is different from that of the outer hole 138. The ejection direction of the inner hole 137 is toward the heat insulation board 131. The “towards the core cabin space 113” in the description of the present embodiment can be regarded as the direction away from the heat insulation board 131.

[0061] Optionally, along the circumferential direction of the outlet pipe 132, the inner holes 137 and the outer holes 138 are alternately arranged, that is, the inner holes 137 and the outer holes 138 are located at different circumferential positions of the outlet pipe 132, and along the circumferential direction of the outlet pipe 132, the holes adjacent to the inner hole 137 on both sides are the outer holes 138, and the holes adjacent to the outer hole 138 on both sides are the inner holes 137. At the same time, the inner holes 137 and the outer holes 138 are evenly distributed along the circumferential direction of the outlet pipe 132.

[0062] Specifically, the central angle corresponding to the adjacent inner holes 137 and the outer holes 138 on the first outlet pipe 1321 is α, 10°≤α≤20°, and α can be set to 10°, 15° or 20°. The central angle corresponding to the adjacent inner holes 137 and the outer holes 138 on the second outlet pipe 1322 is β, 10°≤β≤20°, and β can be set to 10°, 15° or 20°. The central angle corresponding to the adjacent inner holes 137 and the outer holes 138 on the third outlet pipe 1323 is γ, 10°≤γ≤20°, and γ can be set to 10°, 15° or 20°. The "central angle" referred to in this embodiment refers to the angle formed by the line connecting the centers of the annular structure formed by the position of the inner hole 137 and the outlet pipe 132 and the line connecting the centers of the annular structure formed by the position of the outer hole 138 and the outlet pipe 132.

[0063] Please refer to Figure 1 and Figure 2In the present embodiment, the connection positions between the heat-insulating and flow-guiding structure 130 and the air bleed branch pipe 123 are both located at the top of the engine casing 111. Specifically, the air collecting shell 125 is located at the top of the heat-insulating and flow-guiding structure 130, and the top is the upward direction when the aircraft engine is installed and used. By setting the connection position at the top, it helps to make the ejection amount of the external gas at various locations of the outlet pipe 132 more consistent, thereby ensuring the cooling effect at various locations in the core cabin space 113. Furthermore, since the air collecting shell 125 is located at the top of the heat-insulating and flow-guiding structure 130, in order to facilitate the arrangement of the air bleed main pipe 121 and the air bleed branch pipe 123, in the present embodiment, the position where the air bleed main pipe 121 passes through the core cabin cover 112 is located at the top of the core cabin cover 112.

[0064] The ventilation and heat dissipation device 100 of the nacelle core cabin and the aircraft engine provided by the embodiment of the present invention, when it is necessary to cool the compressor section 133, the bleed air main pipe 121 is connected to the first air collecting shell 1251 by controlling the multi-way valve 122, and the external bypass gas introduced by the bleed air main pipe 121 passes through the multi-way valve 122, the bleed air branch pipe 123 and the first air collecting shell 1251 in sequence to enter the first outlet pipe 1321, flows along the circumferential direction of the first outlet pipe 1321, and is ejected from the inner hole 137 and the outer hole 138, so as to achieve effective cooling of the compressor section 133; when it is necessary to cool the combustion chamber section 134, the bleed air main pipe 121 is connected to the second air collecting shell 1252 ... The multi-way valve 122, the bleed air branch pipe 123 and the second air collecting shell 1252 enter the second outlet pipe 1322, flow along the circumferential direction of the second outlet pipe 1322, and are ejected from the inner hole 137 and the outer hole 138, thereby effectively cooling the compressor section 133; when it is necessary to cool the turbine section 135, the bleed air main pipe 121 is connected to the third air collecting shell 1253 by controlling the multi-way valve 122, and the external bypass gas introduced by the bleed air main pipe 121 passes through the multi-way valve 122, the bleed air branch pipe 123 and the third air collecting shell 1253 in turn, enters the third outlet pipe 1323, flows along the circumferential direction of the third outlet pipe 1323, and is ejected along the inner hole 137 and the outer hole 138, thereby effectively cooling the turbine section 135 (including the high-pressure turbine and the low-pressure turbine). The external gas entering the core cabin space 113 from the first outlet pipe 1321, the second outlet pipe 1322 and the third outlet pipe 1323 eventually flows out from the exhaust gap 114, thereby enhancing the ventilation effect in the core cabin space 113 and reducing the accumulation of flammable vapor.

[0065] Figure 7 The flowchart of the heat dissipation control method of the nacelle core cabin provided by this embodiment is shown. Figure 1-Figure 7An embodiment of the present invention further provides a heat dissipation control method for a nacelle core cabin, which is used to control the multi-way valve 122 in the ventilation and heat dissipation device 100 of the above-mentioned nacelle core cabin. Accordingly, a controller 124 for executing the heat dissipation control method for the nacelle core cabin is also provided at the multi-way valve 122.

[0066] Specifically, the heat dissipation control method of the nacelle core cabin includes:

[0067] S01: Detect and determine whether the temperatures of the compressor part, the combustion chamber part and the turbine part exceed threshold values.

[0068] By detecting and judging whether the temperature of the compressor part exceeds the threshold value, whether the temperature of the combustion chamber part exceeds the threshold value, and whether the temperature of the turbine part exceeds the threshold value. In this embodiment, the compressor part is the part of the nacelle core cabin corresponding to the compressor position along the axial direction L, which includes the casing part, accessories, and cables located in the corresponding space; the combustion chamber part is the part of the nacelle core cabin corresponding to the combustion chamber position along the axial direction L, which includes the casing part, accessories, and cables located in the corresponding space; the turbine part is the part of the nacelle core cabin corresponding to the combustion chamber position along the axial direction L, which includes the casing part, accessories, and cables located in the corresponding space.

[0069] The following describes step S01 by taking the process of detecting and judging whether the temperature of the compressor part exceeds the threshold as an example. The detection and judgment process of the combustion chamber part and the turbine part is basically the same as that of the compressor part, and will not be repeated here.

[0070] The steps of detecting the temperature of the compressor part and judging whether it exceeds the threshold value include: during the operation of the aircraft engine, the temperature is detected in real time by the onboard temperature sensor to obtain the real-time temperature of the components with the onboard temperature sensor. If the key accessories or casings of the compressor part are equipped with onboard temperature sensors, it is judged whether it exceeds the threshold value according to the temperature signal detected by the temperature sensor. If the key accessories or parts of the casing of the compressor part are not equipped with onboard temperature sensors, the operating conditions of the key accessories without onboard temperature sensors when the temperature exceeds the threshold value can be determined during the test verification stage based on the temperature detection data of the onboard temperature sensor and the operating power of the aircraft engine and other parameters, so as to judge whether it exceeds the threshold value. Specifically, the specific value of the threshold value is set according to the actual operation requirements.

[0071] S02 : When the temperature of the compressor part exceeds a threshold value, the multi-way valve 122 is controlled to connect the bleed air branch pipe 123 connected to the first flow channel with the bleed air main pipe 121 .

[0072] When executing step S01 and determining that the temperature of the compressor part exceeds the threshold value, a control signal is sent to the multi-way valve 122 through the controller 124, and the multi-way valve 122 connects an air bleed branch pipe 123 with the air bleed main pipe 121. The air bleed branch pipe 123 is connected with the first outlet pipe 1321 through the first air collecting shell 1251. At this time, the external gas introduced by the air bleed main pipe 121 flows into the air bleed branch pipe 123 through the multi-way valve 122, and enters the first outlet pipe 1321 after passing through the first air collecting shell 1251, and is ejected along the inner hole 137 and the outer hole 138 of the first outlet pipe 1321, thereby cooling the compressor part.

[0073] S03 : When the temperature of the combustion chamber exceeds a threshold value, the multi-way valve 122 is controlled to connect the bleed air branch pipe 123 communicating with the second flow passage and the bleed air main pipe 121 .

[0074] When executing step S01 and determining that the temperature of the combustion chamber exceeds the threshold, the controller 124 sends a control signal to the multi-way valve 122, and the multi-way valve 122 connects an air bleed branch pipe 123 with the air bleed main pipe 121. The air bleed branch pipe 123 is connected to the second outlet pipe 1322 through the second air collecting shell 1252. At this time, the external gas introduced by the air bleed main pipe 121 flows into the air bleed branch pipe 123 through the multi-way valve 122, and enters the second outlet pipe 1322 after passing through the second air collecting shell 1252, and is ejected along the inner hole 137 and the outer hole 138 of the second outlet pipe 1322, thereby cooling the combustion chamber.

[0075] S04 : When the temperature of the turbine part exceeds a threshold value, the multi-way valve 122 is controlled to connect the bleed air branch pipe 123 connected to the third flow passage with the bleed air main pipe 121 .

[0076] When executing step S01 and determining that the temperature of the turbine part exceeds the threshold value, a control signal is sent to the multi-way valve 122 through the controller 124, and the multi-way valve 122 connects an air bleed branch pipe 123 with the air bleed main pipe 121, and the air bleed branch pipe 123 is connected with the third outlet pipe 1323 through the third air collecting shell 1253. At this time, the by-pass gas introduced into the air bleed main pipe 121 flows into the air bleed branch pipe 123 through the multi-way valve 122, and enters the third air collecting shell 1253. After entering the air collecting shell 125, part of the by-pass gas enters the high-pressure turbine outlet pipe 1324, and the other part enters the low-pressure turbine outlet pipe 1325, and is ejected through the inner hole 137 and the outer hole 138 of the high-pressure turbine outlet pipe 1324 and the low-pressure turbine outlet pipe 1325, so as to cool down the turbine part.

[0077] In the above steps, step S02, step S03 and step S04 are executed in parallel, that is, whether step S02 is executed does not have a decisive influence on the execution of step S03 and step S04, whether step S03 is executed does not have a decisive influence on the execution of step S02 and step S04, and whether step S04 is executed does not have a decisive influence on the execution of step S03 and step S04. At the same time, after executing step S02, step S03 or step S04, if it is detected that the temperature of the corresponding part is lower than the threshold, a control signal can be sent to the multi-way valve 122 through the controller 124 to disconnect the corresponding air bleed branch pipe 123 from the air bleed main pipe 121.

[0078] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A ventilation and heat dissipation device for a nacelle core cabin, characterized in that: A core cabin space is formed between the engine casing and the core cabin cover in the core cabin, and an exhaust gap connects the core cabin space with the external atmospheric environment; The ventilation and heat dissipation device of the nacelle core cabin is arranged in the core cabin space and includes: An air bleed main pipe, one end of which passes through the core nacelle cover to introduce external air; A multi-way valve and a plurality of air bleed branches connected to the multi-way valve, the air bleed main pipe and the multi-way valve, and the multi-way valve is used to control the opening and closing of the air bleed main pipe and the air bleed branch pipe; and A heat-insulating flow-guiding structure, wherein the heat-insulating flow-guiding structure wraps the engine casing; the heat-insulating flow-guiding structure has a compressor section, a combustion chamber section and a turbine section which are connected in sequence, and the heat-insulating flow-guiding structure has a first flow channel arranged around the compressor section, a second flow channel arranged around the combustion chamber section and a third flow channel arranged around the turbine section, the first flow channel, the second flow channel and the third flow channel are respectively connected to the multi-way valve through an air bleed branch pipe, and the first flow channel, the second flow channel and the third flow channel are respectively used to spray the outer bypass gas into the core cabin space.

2. The ventilation and heat dissipation device of the nacelle core cabin according to claim 1, characterized in that: The heat insulation and flow guiding structure includes a heat insulation plate and a plurality of outlet pipes, wherein the heat insulation plate is arranged to wrap the engine casing, and the heat insulation plate has the compressor section, the combustion chamber section and the turbine section; the plurality of outlet pipes are arranged in the compressor section to form the first flow channel, the plurality of outlet pipes are arranged in the combustion chamber section to form the second flow channel, and the plurality of outlet pipes are arranged in the turbine section to form the third flow channel.

3. The ventilation and heat dissipation device of the nacelle core cabin according to claim 2, characterized in that: The outlet pipe is detachably connected to the heat insulation board.

4. The ventilation and heat dissipation device of the nacelle core cabin according to claim 2, characterized in that: The outlet pipe is provided with a plurality of inner holes and a plurality of outer holes. The plurality of inner holes are arranged toward the heat insulation board so as to spray the outer duct gas toward the heat insulation board; the plurality of outer holes are arranged toward the core cabin space so as to spray the outer duct gas toward the core cabin space.

5. The ventilation and heat dissipation device of the nacelle core cabin according to claim 4, characterized in that: Along the circumferential direction of the outlet pipe, the inner holes and the outer holes are arranged alternately.

6. The ventilation and heat dissipation device of the nacelle core cabin according to claim 4, characterized in that: The outlet pipe forming the first flow channel is the first outlet pipe, and the central angle corresponding to the adjacent inner holes and outer holes on the first outlet pipe is α, 10°≤α≤20°; and / or, The outlet pipe forming the second flow channel is a second outlet pipe, and the central angle corresponding to the adjacent inner holes and outer holes on the second outlet pipe is β, 10°≤β≤20°; The outlet pipe forming the third flow channel is the third outlet pipe, and the central angle corresponding to the adjacent inner holes and the external measurement and control holes on the third outlet pipe is γ, and 10°≤γ≤20°.

7. The ventilation and heat dissipation device of the nacelle core cabin according to claim 2, characterized in that: The outlet pipe is a ring-shaped pipe connected end to end, and the first flow channel, the second flow channel and the third flow channel are respectively formed by a plurality of outlet pipes arranged side by side; an air collecting shell is arranged at one end of the air inlet branch pipe away from the multi-way valve, and the air collecting shell has an air collecting cavity and a plurality of air outlet notches connected to the air collecting cavity, and the air collecting cavity is connected to the air inlet branch pipe; the outlet pipe is clamped to the air outlet notch, and is connected to the air collecting cavity through the air outlet notch; Among them, the air collecting shell connected to the first flow channel is the first air collecting shell, and the number of air outlet notches on the first air collecting shell is consistent with the number of outlet pipes of the first flow channel; the air collecting shell connected to the second flow channel is the second air collecting shell, and the number of air outlet notches on the second air collecting shell is consistent with the number of outlet pipes of the second flow channel; the air collecting shell connected to the third flow channel is the third air collecting shell, and the number of air outlet notches on the third air collecting shell is consistent with the number of outlet pipes of the third flow channel.

8. The ventilation and heat dissipation device of the nacelle core cabin according to claim 2, characterized in that: The number of outlet pipes included in the first flow channel is a, 4≤a≤6; and / or, The number of outlet pipes included in the second flow channel is b, 2≤b≤3; and / or, A portion of the outlet pipes included in the third flow channel are high-pressure turbine outlet pipes, and another portion are low-pressure turbine outlet pipes; the number of high-pressure turbine outlet pipes is c, 2≤c≤3; the number of low-pressure turbine outlet pipes is d, 4≤d≤6.

9. The ventilation and heat dissipation device of the nacelle core cabin according to claim 1, characterized in that: The communication position between the heat insulation and flow guiding structure and the air bleed branch pipe is located at the top of the engine casing.

10. An aircraft engine, characterized in that: The aircraft engine comprises a core cabin and a ventilation and heat dissipation device of the nacelle core cabin as described in any one of claims 1-9.

11. A method for controlling heat dissipation of a nacelle core cabin, used to control a multi-way valve in a ventilation and heat dissipation device of a nacelle core cabin according to any one of claims 1 to 9; characterized in that: The heat dissipation control method of the nacelle core cabin comprises: Detect and determine whether the temperatures of the compressor part, the combustion chamber part, and the turbine part exceed the threshold value; When the temperature of the compressor part exceeds a threshold value, controlling the multi-way valve to connect the bleed air branch pipe connected to the first flow channel with the bleed air main pipe; When the temperature of the combustion chamber portion exceeds a threshold value, controlling the multi-way valve to connect the bleed air branch pipe connected to the second flow channel with the bleed air main pipe; When the temperature of the turbine part exceeds a threshold value, the multi-way valve is controlled to connect the bleed air branch pipe connected to the third flow passage with the bleed air main pipe.

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