CN118089439A - Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine - Google Patents
Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine Download PDFInfo
- Publication number
- CN118089439A CN118089439A CN202410422089.4A CN202410422089A CN118089439A CN 118089439 A CN118089439 A CN 118089439A CN 202410422089 A CN202410422089 A CN 202410422089A CN 118089439 A CN118089439 A CN 118089439A
- Authority
- CN
- China
- Prior art keywords
- oil
- heat exchanger
- oil delivery
- archimedes spiral
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000000446 fuel Substances 0.000 title claims description 22
- 239000003921 oil Substances 0.000 claims abstract description 79
- 230000000712 assembly Effects 0.000 claims abstract description 19
- 238000000429 assembly Methods 0.000 claims abstract description 19
- 239000000295 fuel oil Substances 0.000 claims abstract description 11
- 230000000694 effects Effects 0.000 abstract description 6
- 230000007547 defect Effects 0.000 abstract description 2
- 238000001816 cooling Methods 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 4
- 208000006990 cholangiocarcinoma Diseases 0.000 description 3
- 239000000306 component Substances 0.000 description 3
- 208000009854 congenital contractural arachnodactyly Diseases 0.000 description 3
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000077 insect repellent Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention discloses an Archimedes spiral type air-fuel oil heat exchanger for an aviation gas turbine engine, which comprises a cylindrical outer shell, wherein a plurality of heat exchange modules are arranged in the cylindrical outer shell, a plurality of oil delivery pipes are arranged in the heat exchange modules along the axis of the cylindrical outer shell, each oil delivery pipe consists of two oil delivery pipe assemblies in the shape of Archimedes spiral which are symmetrical in center, the inner side ends of the two oil delivery pipe assemblies are connected, the outer side ends of the two oil delivery pipe assemblies are respectively connected with an oil inlet pipe and an oil outlet pipe, the oil inlet pipe and the oil outlet pipe are respectively connected to two oil collecting pipes arranged outside the cylindrical outer shell, and supporting sheets are arranged in gaps of adjacent oil delivery pipe assemblies. The invention can improve the defects of the prior art, and has simple structure, convenient disassembly and assembly and good heat exchange effect.
Description
Technical Field
The invention relates to the technical field of heat exchanger structural design, in particular to an Archimedes spiral type air-fuel heat exchanger for an aviation gas turbine engine.
Background
With the development of aero gas turbine engine technology, the temperature before the turbine is further increased to obtain more excellent performance, and higher requirements are put on cooling of hot end components of the aero engine such as turbine blades. A blast of air is led out from the outlet of the air compressor as cooling air to cool the high-temperature component, and along with the increase of the temperature of the high-temperature component, the quality of the cooling air is required to be higher. The CCA technology is used for cooling the cooling air led out by the air compressor, and the outer duct air or fuel oil is used as a cold source to exchange heat with the high-temperature cooling air, so that the low-temperature cooling air with higher quality is obtained. One of the core components of CCA technology is an air-to-air heat exchanger and an air-to-fuel heat exchanger. With the development of CCA technology, higher requirements are put on the designed heat exchanger, specifically expressed in: the heat exchanger has high compactness, high structural strength, high vibration level tolerance, good heat exchange effect and low weight, and can adapt to the working conditions of ultrahigh temperature and high pressure; the internal structural space of the engines of different models is different, and the engines of the same type can redesign the heat exchanger according to different sizes, so that the novel heat exchanger with the structure is wider in application range, simple in structure and convenient to assemble and disassemble.
Disclosure of Invention
The invention aims to solve the technical problem of providing an Archimedes spiral type air-fuel heat exchanger for an aviation gas turbine engine, which can solve the defects of the prior art, and has the advantages of simple structure, convenient disassembly and assembly and good heat exchange effect.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows.
The Archimedes spiral type air-fuel oil heat exchanger for the aviation gas turbine engine comprises a cylindrical outer shell, wherein a plurality of heat exchange modules are arranged in the cylindrical outer shell, a plurality of oil delivery pipes are arranged in the heat exchange modules along the axis of the cylindrical outer shell and consist of two oil delivery pipe assemblies in the shape of Archimedes spiral which are symmetrical in center, the inner side ends of the two oil delivery pipe assemblies are connected, the outer side ends of the two oil delivery pipe assemblies are respectively connected with an oil inlet pipe and an oil outlet pipe, the oil inlet pipe and the oil outlet pipe are respectively connected to two oil collecting pipes arranged outside the cylindrical outer shell, and supporting sheets are arranged in gaps of adjacent oil delivery pipe assemblies.
Preferably, the fuel flow directions in the adjacent fuel delivery pipes are opposite.
Preferably, 5 heat exchange modules are arranged in the cylindrical outer shell, and 5 oil delivery pipes are arranged in the heat exchange modules.
Preferably, 4 supporting plates are arranged in the gaps of the adjacent oil delivery pipe assemblies, the adjacent supporting plates in the same gaps are mutually perpendicular, and the included angle between each supporting plate and the adjacent oil inlet pipe or oil outlet pipe is 45 degrees.
Preferably, a U-shaped bayonet is arranged at the joint of the supporting piece and the oil delivery pipe assembly.
Preferably, the axial section of the oil collecting pipe is semicircular.
The beneficial effects brought by adopting the technical scheme are as follows:
The compactness of the heat exchanger is greater than 300m 2/m3, the compactness is high, the heat exchanger has larger heat exchange area under the same volume condition, and the requirement of the aviation gas turbine engine on the space occupied by the built-in heat exchanger can be better met.
The heat exchanger has the advantages that the multiple rows of oil delivery pipes inside the heat exchanger are closely arranged, the U-shaped supporting plate structures are arranged in the gaps between the multiple rows of oil delivery pipes, the structural strength of the heat exchanger is improved, the structural weight of the heat exchanger is reduced, meanwhile, the high-vibration-level environment inside the aero-engine can be met, and the requirements of high structural strength, high-vibration-level tolerance and low weight of the aero-gas turbine engine can be met.
The fuel side of the heat exchanger adopts an Archimedes spiral thin round bent pipe, the existing Archimedes spiral heat exchanger can only realize cold and hot fluid cross flow design, and the heat exchanger achieves the effects of local cross flow and integral countercurrent through structural design, thereby greatly enhancing the heat exchange effect and meeting the requirements of an aeroengine on the heat exchange performance of the heat exchanger; the circular tube structure has good pressure resistance, and can meet the requirement of high-pressure fuel in the aero-engine on the structural strength of the fuel side pipeline.
The heat exchanger adopts a unit modularized design, is formed by repeatedly stacking single unit heat exchange modules, has a simple structure, can be assembled in a blocking way, is convenient and easy to detach, has a wide application range, can meet different application scenes of aviation gas turbine engines of different sizes of different models, and only needs to change the number of the unit heat exchange modules to fill the whole space for cylindrical heat exchanger spaces of different sizes.
The air side flow of the heat exchanger is free of bending, the flow resistance is small, the requirement of the aeroengine on air flow pressure loss can be met, meanwhile, the air side air flow is uniformly distributed in space, an air corridor is prevented from being formed, and the normal operation of the heat exchanger can be ensured.
Drawings
Fig. 1 is a schematic external view of the present invention.
Fig. 2 is a schematic view of a heat exchanger structure with an outer casing removed.
FIG. 3 is a schematic view of a single heat exchange module with the support sheet removed.
Fig. 4 is a front view of a single heat exchange module.
Fig. 5 is a right side view of a single heat exchange module with the support sheet removed.
Fig. 6 is a top view of a single heat exchange module with the support sheet removed.
Fig. 7 is a schematic structural view of a single-row oil delivery pipe assembly.
Fig. 8 is a schematic view showing an arrangement of support plates in the heat exchange module.
Fig. 9 is a schematic view of a single support sheet structure.
Detailed Description
Referring to fig. 1-9, a specific embodiment of the present invention includes a cylindrical outer shell 11, 5 heat exchange modules 12 are installed in the cylindrical outer shell 11, 5 oil delivery pipes 201 are arranged in the heat exchange modules 12 along the axis of the cylindrical outer shell 11, the oil delivery pipes 201 are composed of two oil delivery pipe assemblies 301 with archimedes spiral shapes and symmetrical in center, inner ends of the two oil delivery pipe assemblies 301 are connected, outer ends of the two oil delivery pipe assemblies 301 are respectively connected with an oil inlet pipe 14 and an oil outlet pipe 15, the oil inlet pipe 14 and the oil outlet pipe 15 are respectively connected to two oil collecting pipes 13 arranged outside the cylindrical outer shell 11, 4 support pieces 202 are installed in gaps of adjacent oil delivery pipe assemblies 301, adjacent support pieces 202 in the same gap are mutually perpendicular, and an included angle between each support piece 202 and an adjacent oil inlet pipe 14 or an oil outlet pipe 15 is 45 °. The joint of the supporting piece 202 and the oil delivery pipe assembly 301 is provided with a U-shaped bayonet.
The main application scene and the installation position of the heat exchanger are cylindrical heat exchange space in the engine, which is different from the common circular heat exchange space. The clearance between the cylindrical outer shell 11 and the heat exchange module 12 of the Archimedes spiral type in the heat exchange module 12 needs to be reduced as far as possible, and the clearance needs to be matched with the radial distance between the oil delivery pipes 201 in the heat exchange module 12 so as to prevent the too large clearance from forming an air passage, which causes the too high air flow rate ratio, from influencing the heat exchange performance of the heat exchanger due to the too small air flow rate passing through the air flow passage in the heat exchanger. A plurality of identical heat exchange modules 12 are closely arranged at equal intervals along the axial direction of the cylindrical outer shell 11. The number of repetitions of the heat exchange module 12 can also be changed according to different application scenarios proposed by aviation gas turbine engines of different models, so that the whole cylindrical space is preferably completely filled, and the compactness of the heat exchanger can be improved.
The adjacent oil delivery pipes 201 are connected in a serpentine manner, so that the fuel flow directions in the adjacent oil delivery pipes are opposite, and the connection positions are connected by straight pipes; the fuel oil flow direction of the fuel oil of the 5 groups of the fuel oil pipes 201 is changed to be 4 times, so that the effect of local cross flow and total countercurrent is achieved; the cross-shaped support plates 202 can improve the structural strength and vibration resistance of the heat exchanger.
The oil delivery pipe 201 is composed of two oil delivery pipe assemblies 301 which are symmetrical in center and are connected at the center point, has the structural characteristics similar to mosquito-repellent incense, and the distance between adjacent pipelines in the oil delivery pipe 201 is small so as to improve the compactness of the heat exchanger; the gaps between adjacent tubes form air flow channels when the oil delivery tubes 201 are stacked in the axial direction, the air flow channels being unbent to reduce air-side flow resistance.
The oil collecting pipe 13 connects a plurality of oil inlet pipes 14 to form an inlet oil collecting pipe, connects a plurality of oil outlet pipes 15 to form an outlet oil collecting pipe, the axial section of the oil collecting pipe 13 is semicircular, the pipe diameter and the pipe wall of the oil collecting pipe are both larger than those of the oil conveying pipe inside the heat exchanger, and the oil collecting pipe can provide larger structural strength and bear larger fuel flow.
During operation, high-temperature cooling air led out from the outlet of the air compressor enters the cylindrical shell 11 along the axial direction, passes through an air flow channel formed by gaps of the oil conveying pipe 201, exchanges heat with low-temperature fuel oil in the heat exchange modules 12 of a plurality of Archimedes spirals, and enters high-temperature parts of the engine to cool the high-temperature parts in the engine. The flow direction of the air is perpendicular to the flow direction of the fuel oil from the local view, and the cross flow type fuel oil is adopted; in general, the overall flow direction of the fuel is serpentine, the flow direction of the fuel is opposite to the flow direction of the air, the number of times of changing the overall flow direction of the fuel is 4, and the flow condition of the fuel and the air can be regarded as countercurrent in engineering; the heat exchanger flow conditions are local cross flow and total countercurrent.
The foregoing has shown and described the basic principles and main features of the present invention and the advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. The Archimedes spiral type air-fuel oil heat exchanger for the aviation gas turbine engine comprises a cylindrical outer shell (11), wherein a plurality of heat exchange modules (12) are installed in the cylindrical outer shell (11), and the Archimedes spiral type air-fuel oil heat exchanger is characterized in that: the heat exchange module (12) is internally provided with a plurality of oil delivery pipes (201) along the axis of the cylindrical outer shell (11), each oil delivery pipe (201) is composed of two oil delivery pipe assemblies (301) in the shape of Archimedes spiral with central symmetry, the inner side ends of the two oil delivery pipe assemblies (301) are connected, the outer side ends of the two oil delivery pipe assemblies (301) are respectively connected with an oil inlet pipe (14) and an oil outlet pipe (15), the oil inlet pipe (14) and the oil outlet pipe (15) are respectively connected to two oil collecting pipes (13) arranged outside the cylindrical outer shell (11), and supporting plates (202) are arranged in gaps of adjacent oil delivery pipe assemblies (301).
2. An archimedes spiral air-fuel heat exchanger for an aircraft gas turbine engine according to claim 1, characterized in that: the fuel flow directions in the adjacent oil delivery pipes (201) are opposite.
3. An archimedes spiral air-fuel heat exchanger for an aircraft gas turbine engine according to claim 1, characterized in that: 5 heat exchange modules (12) are arranged in the cylindrical shell body (11), and 5 oil delivery pipes (201) are arranged in the heat exchange modules (12).
4. An archimedes spiral air-fuel heat exchanger for an aircraft gas turbine engine according to claim 1, characterized in that: and 4 supporting plates (202) are arranged in the gaps of the adjacent oil delivery pipe assemblies (301), the adjacent supporting plates (202) in the same gap are mutually perpendicular, and the included angle between each supporting plate (202) and the adjacent oil inlet pipe (14) or the adjacent oil outlet pipe (15) is 45 degrees.
5. An archimedes spiral air-fuel heat exchanger for aviation gas turbine engines as in claim 4, wherein: the U-shaped bayonet is arranged at the joint of the supporting piece (202) and the oil delivery pipe assembly (301).
6. An archimedes spiral air-fuel heat exchanger for an aircraft gas turbine engine according to claim 1, characterized in that: the axial section of the oil collecting pipe (13) is semicircular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410422089.4A CN118089439A (en) | 2024-04-09 | 2024-04-09 | Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410422089.4A CN118089439A (en) | 2024-04-09 | 2024-04-09 | Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118089439A true CN118089439A (en) | 2024-05-28 |
Family
ID=91155072
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410422089.4A Pending CN118089439A (en) | 2024-04-09 | 2024-04-09 | Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118089439A (en) |
-
2024
- 2024-04-09 CN CN202410422089.4A patent/CN118089439A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110081461B (en) | Method and system for radial tubular heat exchanger | |
| CN106958486B (en) | Use the method for circular heat exchanger cooling fluid | |
| CN110553519B (en) | Tube bundle type heat exchanger | |
| US11248850B2 (en) | Heat exchanger with interspersed arrangement of cross-flow structures | |
| CN105222616B (en) | Method and system for radial tubular duct heat exchanger | |
| JP6685290B2 (en) | Spiral crossflow heat exchanger | |
| CN105043143B (en) | Pipe type air-air heat exchanger in annular channel | |
| WO2013158916A1 (en) | Helical tube egr cooler | |
| CN101705870A (en) | Air-oil heat exchanger suitable for gas turbine engine | |
| US10233839B2 (en) | Composite heat exchanger | |
| CN112050255B (en) | Flame tube adopting clearance rotational flow cooling | |
| CN110906358A (en) | Air precooler adopting gradient heat exchange material | |
| CN114635799A (en) | Precooler with radial offset arrangement | |
| CN118089439A (en) | Archimedes spiral type air-fuel heat exchanger for aviation gas turbine engine | |
| CN217002071U (en) | Precooler that radial offset was arranged | |
| CN104612834A (en) | Spiral tube heat exchanger suitable for aviation engine | |
| US5097896A (en) | Heat exchanger | |
| EP4047296A1 (en) | Fluid cooler for a gas turbine engine | |
| CN107192279A (en) | A kind of circular passage inside spin shell and tube gas-gas heat exchanger | |
| CN115949506A (en) | Aircraft engine draws gas cooling heat exchanger | |
| EP3730764A1 (en) | Gas turbine with multi-stage radial compressor and inter-compressor cross-over pipe heat exchanger | |
| CN111156614B (en) | Heat exchanger and air conditioner outdoor unit | |
| CN107131776A (en) | Double helix tubular type gas-gas heat exchanger in a kind of circular passage | |
| CN114526628A (en) | Heat exchanger and manufacturing method and application thereof | |
| CN115711178A (en) | Gaseous fuel engine fuel manifold and engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |