CN-117446150-B - Heat-proof and insulating structure between fuselage and wing

Abstract

The invention relates to an anti-heat insulation structure between a fuselage and a wing, which comprises at least one heat exchange tube, wherein the heat exchange tube comprises an evaporation end and a condensation end, the evaporation end is arranged at the fuselage close to an engine tail flame or a jet tube, the condensation end is arranged at the wing where anti-icing and deicing are required, the heat exchange tube also comprises a liquid channel and a steam channel, the liquid channel wraps the steam channel, and the heat exchange is carried out between the fuselage and the wing by utilizing the principle of capillary suction. According to the invention, the liquid working medium in the evaporation end absorbs heat transmitted to a nearby engine body by the engine tail flame or the spray pipe, so that the structure temperature is controlled, the material selection limitation caused by temperature rise is improved, the heat can be further utilized, meanwhile, the condensation end is arranged at the wing where anti-icing and deicing are required, and the heat is used for anti-icing and deicing, so that the air entraining of an engine air compressor can be reduced, the increase of oil consumption caused by the large utilization of the air entraining of the engine in the prior art is avoided, and the cost is reduced.

Inventors

• A RONG
• QI BIN
• ZHANG ZHIXIAN
• REN KUN
• SHANG YIRAN
• HOU YANZE
• SHI YONG

Assignees

• 中国空间技术研究院

Dates

Publication Date

20260508

Application Date

20231124

Claims (7)

1. 1. An anti-heat insulation structure between a fuselage and a wing, which is characterized by comprising at least one heat exchange tube (10), wherein the heat exchange tube (10) comprises an evaporation end (101) and a condensation end (102), the evaporation end (101) is arranged at the fuselage (20) close to an engine tail flame or a jet pipe, and the condensation end (102) is arranged at the wing (30) needing anti-icing and deicing; The heat exchange tube (10) further comprises a liquid channel (103) and a vapor channel (104), the liquid channel (103) wrapping the vapor channel (104); -exchanging heat between said fuselage (20) and said wing (30) using the principle of capillary suction; The evaporation end (101) is of a multi-section bent U-shaped structure; the condensing end (102) is provided with an outer shell (1021), and a mounting interface (1022) for connecting with the tail wing is arranged on the outer shell (1021); the section of the outer shell (1021) is of a V-shaped structure matched with the tail wing.
2. 2. The heat insulation structure between a fuselage and a wing according to claim 1, wherein a heat insulation section (105) is arranged between the evaporation end (101) and the condensation end (102), and the heat insulation section (105) is externally wrapped with heat insulation material.
3. 3. The structure for preventing and insulating heat between a fuselage and a wing according to claim 2, wherein the insulating section (105) is disposed in a cabin between the fuselage (20) and the wing (30) so as not to contact with both the fuselage (20) and the wing (30).
4. 4. The structure according to claim 2, wherein the evaporation end (101) is provided with at least one evaporator, any one of which is connected to the fuselage (20) near the engine tail flame or nozzle by a heat-conducting material, or The evaporator is embedded inside the skin of the fuselage (20) close to the engine tail flame or nozzle.
5. 5. The structure according to claim 4, wherein the condensation end (102) is provided with at least one condenser, any condenser is connected with the wing (30) to be subjected to anti-icing and deicing by heat conducting material, or The condenser is integrally arranged with the wing (30) to be subjected to anti-icing and deicing.
6. 6. The structure for thermal insulation between fuselage and wing according to claim 5, characterized in that the liquid channel (103) delivers the working medium cooled and liquefied by the condenser to the evaporator by capillary suction.
7. 7. The structure for preventing and insulating heat between a fuselage and a wing according to claim 5, The mounting interfaces (1022) are countersunk, and the mounting interfaces (1022) are symmetrically arranged on two sides of the V-shaped structure.

Description

Heat-proof and insulating structure between fuselage and wing Technical Field The invention relates to the technical field of aircraft skin heat exchange management structures, in particular to a heat-proof and insulation structure between a fuselage and a wing. Background In general, a safe distance is arranged between the engine nacelle and the fuselage structure to ensure that the fuselage structure is not affected by the high temperature of the tail flame. With rapid development of flying speed and altitude of aircrafts, new requirements are put forward on engine nacelle hanging. In order to reduce the height of the engine, the distance between the engine nacelle and the engine body is required to be reduced as far as possible for the structure of installing the engine nacelle on the engine belly or the engine back. And engine tail flame temperatures up to 800 ℃ or more, resulting in a fuselage structure having a structural temperature of 150 ℃ or more proximate to the engine tail flame region. If the design of the heat-proof structure is not adopted, the traditional aluminum alloy structure is difficult to adapt to the high temperature of the tail flame influence area. If the method of replacing the structural material is adopted, great cost and weight are paid. Therefore, it is necessary to design an anti-heat insulation structure to transmit the heat load of the tail flame influence area to the tail front edge and other parts requiring anti-icing and deicing. Disclosure of Invention In order to solve the technical problems in the prior art, the invention aims to provide an anti-heat insulation structure between a machine body and a machine wing, which can realize heat exchange between the machine body and the machine wing, on one hand, control the temperature of the machine body structure to meet the allowable requirement of aluminum alloy, and on the other hand, reduce the hot air bleed amount of an engine for anti-icing and deicing. In order to achieve the above object, the present invention provides an insulation structure between a fuselage and a wing, which is disposed on an aircraft. The heat-proof and heat-insulating structure comprises at least one heat exchange tube, the heat exchange tube comprises an evaporation end and a condensation end, the evaporation end is arranged at a machine body close to an engine tail flame or a spray pipe, and the condensation end is arranged at a wing where anti-icing and deicing are required; The heat exchange tube also comprises a liquid channel and a steam channel, wherein the liquid channel wraps the steam channel; heat exchange between the fuselage and the wing is performed using the principle of capillary suction. According to one technical scheme of the invention, an insulation section is arranged between the evaporation end and the condensation end, and an insulation material is wrapped outside the insulation section. According to one aspect of the invention, the insulation section is arranged in a cabin between the fuselage and the wing, and is not in contact with both the fuselage and the wing. According to one aspect of the invention, the evaporation end is provided with at least one evaporator, either of which is connected to the fuselage adjacent to the engine tail flame or nozzle by a thermally conductive material, or The evaporator is embedded inside the skin of the fuselage near the engine tail flame or nozzle. According to one technical scheme of the invention, the evaporation end is of a multi-section bent U-shaped structure. According to one technical scheme of the invention, the condensing end is provided with at least one condenser, and any condenser is connected with the wing needing to be subjected to anti-icing and deicing through a heat-conducting material, or The condenser is integrally arranged with the wing which needs to be subjected to anti-icing and deicing. According to one embodiment of the invention, the liquid channel conveys the working medium cooled and liquefied by the condenser to the evaporator by capillary suction. According to one technical scheme of the invention, the condensing end is provided with an outer shell, and the outer shell is provided with a mounting interface for connecting with the tail wing. According to one technical scheme of the invention, the section of the outer shell is of a V-shaped structure matched with the tail wing; The mounting interfaces are countersunk holes and are symmetrically arranged on two sides of the V-shaped structure. Compared with the prior art, the invention has the following beneficial effects: According to one scheme of the invention, the heat-proof and insulating structure comprises the evaporation end and the condensation end, and liquid working medium in the evaporation end absorbs heat of engine tail flame or jet pipe transmitted to a nearby engine body, so that the temperature of the structure is controlled, the limitation of material selection caused by temperature rise