CN113830311A - Air supply temperature adjusting device and method for general aircraft cabin - Google Patents
Air supply temperature adjusting device and method for general aircraft cabin Download PDFInfo
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- CN113830311A CN113830311A CN202111168580.1A CN202111168580A CN113830311A CN 113830311 A CN113830311 A CN 113830311A CN 202111168580 A CN202111168580 A CN 202111168580A CN 113830311 A CN113830311 A CN 113830311A
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- radiator
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000001105 regulatory effect Effects 0.000 claims abstract description 21
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 238000001816 cooling Methods 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
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- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention provides a device and a method for adjusting the air supply temperature of a general airplane cabin, and belongs to the field of airplane environment control system design. Comprises a flow/pressure regulating valve (1), a primary radiator (2), a secondary radiator (3), a fan (4), a one-way valve (5) and a mixer (6). The flow and pressure of the bleed air of the engine are adjusted through a flow/pressure adjusting valve (1), and the bleed air enters a mixer (6) after being cooled by a first-stage radiator (2) and a second-stage radiator (3); meanwhile, cabin air is drawn to the first-stage radiator (2) under the action of the fan (4) to be used as cold-side airflow, and the cold-side airflow is heated by utilizing the bleed air heat of the engine and then enters the mixer (6). The air of the cabin is circulated to the cold side of the first-stage radiator (2) for heating, so that the air-entraining energy of the engine is fully utilized, and the heating quantity of the system is improved; the air-entraining amount of the engine can be reduced, the size of the radiator is reduced, and the performance compensation loss of the engine is reduced.
Description
Technical Field
The invention belongs to the field of design of an aircraft environment control system, and relates to a device and a method for adjusting the air supply temperature of a general aircraft cabin.
Background
The general airplane generally adopts the engine bleed air after the radiator cooling to heat the cockpit, and the requirement on the air supply temperature of the manned cockpit is limited below 50 ℃. The traditional engine air-entraining heat dissipation mode usually adopts a single-stage radiator and adopts ram air as cold side airflow of the radiator. The scheme has a series of problems in the using process, firstly, most of heat of bleed air of the engine is lost along with ram air, and the heat is not fully utilized. Secondly, for an aircraft with a high demand for heating capacity, the required bleed air quantity of the engine is usually large, so that the compensation loss of the system performance is increased, and when the required quantity exceeds the limit of the bleed air quantity of the engine, additional auxiliary heating equipment needs to be configured, so that the energy consumption on the aircraft is increased.
Disclosure of Invention
The invention provides a device and a method for adjusting the air supply temperature of a general aircraft cabin, which can improve the utilization of the air-entraining heat of an engine and reduce the performance compensation loss of the engine.
The technical scheme adopted by the invention is as follows:
a general air supply temperature adjusting device for an aircraft cabin comprises a flow/pressure adjusting valve 1, a primary radiator 2, a secondary radiator 3, a fan 4, a one-way valve 5 and a mixer 6; the flow/pressure regulating valve 1 is connected with an engine and a first-stage radiator 2, the first-stage radiator 2 is connected with the flow/pressure regulating valve 1, a second-stage radiator 3, a fan 4 and a check valve 5, the second-stage radiator 3 is connected with the first-stage radiator 2 and a mixer 6, the fan 4 is connected with a cabin and the first-stage radiator 2, the check valve 5 is connected with the first-stage radiator 2 and the mixer 6, and the mixer 6 is connected with the second-stage radiator 3, the check valve 5 and the cabin.
The choice of the flow/pressure regulating valve 1 is determined by the cabin air supply flow, the hot side inlet air flow of the primary radiator 2 and the pressure requirement.
The choice of the primary radiator 2 is determined by the outlet air pressure, flow and temperature of the flow/pressure regulating valve 1 and the outlet air pressure, flow and temperature requirements of the fan 4.
The choice of the secondary radiator 3 is determined by the hot side outlet air pressure, flow, temperature of the primary radiator 2 and the inlet air pressure, flow, temperature requirements of the mixer 6.
The selection of the fan 4 is determined by the inlet air pressure and flow requirements of the mixer 6, the flow resistance requirements of the primary heat sink 2.
The volume of the mixer 6 is determined by the cold side outlet air flow and temperature of the primary radiator 2 and the hot side outlet air flow and temperature requirements of the secondary radiator 3.
The function of the check valve 5 is to prevent the hot side outlet air of the secondary radiator 3 from being serially connected to the primary radiator 2 and the fan 4 through the mixer 6 after the fan 4 fails, and damage to equipment is caused.
A general aircraft cabin air supply temperature adjusting method, high-temperature high-pressure air pumped by an engine compressor passes through a flow/pressure adjusting valve 1 to reach the working pressure and flow requirements of a primary radiator 2, precools engine bleed air through the primary radiator 2, and performs secondary heat exchange with ram air through a secondary radiator 3 after precooling, so that the temperature of hot edge outlet air of the secondary radiator 3 meets the requirement of inlet air temperature of a mixer 6, and then the hot edge outlet air enters the mixer 6; the air in the cabin is pumped to the first-stage radiator 2 as cold-side airflow under the action of the fan 4, the air temperature of the cold-side outlet of the first-stage radiator 2 is increased to the requirement of the inlet air temperature of the mixer 6 by utilizing the bleed air heat of the engine, and then the air enters the mixer 6 through the one-way valve 5; the hot side outlet air of the second-stage radiator 3 and the cold side outlet air of the first-stage radiator 2 are fully mixed in the mixer 6 to reach the air supply temperature requirement of the cabin, and are supplied to the cabin to realize heating.
The invention has the advantages that the bleed air energy of the engine is fully utilized, and the heating quantity of the system is improved; the air-entraining amount of the engine can be reduced, the size of the radiator is further reduced, and the performance compensation loss of the engine is reduced.
Drawings
Fig. 1 is a schematic diagram of the principle of a general aircraft cabin supply air temperature regulating device and regulating method of the invention.
Wherein, 1 is a flow/pressure regulating valve, 2 is a first-stage radiator, 3 is a second-stage radiator, 4 is a fan, 5 is a one-way valve, and 6 is a mixer.
Detailed Description
The invention is further described with reference to the following figures.
As shown in fig. 1, a general supply air temperature adjusting device for an aircraft cabin comprises a flow/pressure adjusting valve 1, a primary radiator 2, a secondary radiator 3, a fan 4, a one-way valve 5 and a mixer 6; the flow/pressure regulating valve 1 is connected with an engine and a first-stage radiator 2, the first-stage radiator 2 is connected with the flow/pressure regulating valve 1, a second-stage radiator 3, a fan 4 and a check valve 5, the second-stage radiator 3 is connected with the first-stage radiator 2 and a mixer 6, the fan 4 is connected with a cabin and the first-stage radiator 2, the check valve 5 is connected with the first-stage radiator 2 and the mixer 6, and the mixer 6 is connected with the second-stage radiator 3, the check valve 5 and the cabin.
The choice of the flow/pressure regulating valve 1 is determined by the cabin air supply flow, the hot side inlet air flow of the primary radiator 2 and the pressure requirement.
The choice of the primary radiator 2 is determined by the outlet air pressure, flow and temperature of the flow/pressure regulating valve 1 and the outlet air pressure, flow and temperature requirements of the fan 4.
The choice of the secondary radiator 3 is determined by the hot side outlet air pressure, flow, temperature of the primary radiator 2 and the inlet air pressure, flow, temperature requirements of the mixer 6.
The selection of the fan 4 is determined by the inlet air pressure and flow requirements of the mixer 6, the flow resistance requirements of the primary heat sink 2.
The volume of the mixer 6 is determined by the cold side outlet air flow and temperature of the primary radiator 2 and the hot side outlet air flow and temperature requirements of the secondary radiator 3.
The function of the check valve 5 is to prevent the hot side outlet air of the secondary radiator 3 from being serially connected to the primary radiator 2 and the fan 4 through the mixer 6 after the fan 4 fails, and damage to equipment is caused.
A general aircraft cabin air supply temperature adjusting method, high-temperature high-pressure air pumped by an engine compressor passes through a flow/pressure adjusting valve 1 to reach the working pressure and flow requirements of a primary radiator 2, precools engine bleed air through the primary radiator 2, and performs secondary heat exchange with ram air through a secondary radiator 3 after precooling, so that the temperature of hot edge outlet air of the secondary radiator 3 meets the requirement of inlet air temperature of a mixer 6, and then the hot edge outlet air enters the mixer 6; air in the cabin is pumped to the first-stage radiator 2 to be used as cold-side airflow under the action of the fan 4, and meanwhile, the air temperature of the cold-side outlet of the first-stage radiator 2 is increased to the requirement of the inlet air temperature of the mixer 6 by fully utilizing the bleed air heat of the engine, and then enters the mixer 6 through the one-way valve 5; the hot side outlet air from the secondary radiator 3 and the cold side outlet air from the primary radiator 2 are fully mixed in the mixer 6 to reach the requirement of cabin air supply temperature, and are supplied to the cabin to realize heating.
The above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (8)
1. A general air supply temperature adjusting device for an aircraft cabin is characterized by comprising a flow/pressure adjusting valve (1), a primary radiator (2), a secondary radiator (3), a fan (4), a one-way valve (5) and a mixer (6); flow/pressure regulating valve (1) is connected with engine and one-level radiator (2), one-level radiator (2) and flow/pressure regulating valve (1), second grade radiator (3), fan (4), check valve (5) are connected, second grade radiator (3) and one-level radiator (2), blender (6) are connected, fan (4) and passenger cabin, one-level radiator (2) are connected, check valve (5) and one-level radiator (2), blender (6) are connected, blender (6) and second grade radiator (3), check valve (5) and passenger cabin are connected.
2. A universal aircraft cabin air supply temperature regulating device according to claim 1, characterized in that the choice of flow/pressure regulating valve (1) is determined according to the cabin air supply flow, the hot side inlet air flow of the primary radiator (2) and the pressure requirement.
3. A universal aircraft cabin supply air temperature regulating device according to claim 1, characterized in that the choice of the primary radiator (2) is determined by the outlet air pressure, flow, temperature of the flow/pressure regulating valve (1) and the outlet air pressure, flow, temperature requirement of the fan (4).
4. A universal aircraft cabin supply air temperature regulating device according to claim 1, characterized in that the choice of secondary radiator (3) is determined according to the hot side outlet air pressure, flow, temperature of the primary radiator (2) and the inlet air pressure, flow, temperature requirements of the mixer (6).
5. A universal aircraft cabin supply air temperature adjustment arrangement according to claim 1, characterized in that the selection of the fan (4) is determined in dependence of the inlet air pressure and flow requirements of the mixer (6), the flow resistance requirements of the primary radiator (2).
6. A universal aircraft cabin air supply temperature regulating device as claimed in claim 1, characterised in that the volume of the mixer (6) is determined in dependence on the cold side outlet air flow and temperature of the primary radiator (2), the hot side outlet air flow and temperature requirements of the secondary radiator (3).
7. A universal aircraft cabin supply air temperature regulating device according to claim 1, characterized in that the check valve (5) is used to prevent the hot side outlet air of the secondary radiator (3) from streaming through the mixer (6) to the primary radiator (2) and the fan (4) and causing damage to the equipment after the fan (4) has failed.
8. The adjusting method of the air supply temperature adjusting device for the general-purpose aircraft cabin according to any one of claims 1 to 7, characterized in that high-temperature and high-pressure air pumped by an engine compressor passes through the flow/pressure adjusting valve (1) to meet the working pressure and flow requirements of the primary radiator (2), the engine bleed air is pre-cooled through the primary radiator (2), after pre-cooling, the pre-cooled air passes through the secondary radiator (3) to perform second heat exchange with ram air, so that the hot-side outlet air temperature of the secondary radiator (3) meets the inlet air temperature requirement of the mixer (6), and then enters the mixer (6); air in the cabin is pumped to the first-stage radiator (2) to be used as cold-side airflow under the action of the fan (4), the air temperature of the cold-side outlet of the first-stage radiator (2) is increased to the requirement of the inlet air temperature of the mixer (6) by utilizing the bleed air heat of the engine, and then the air enters the mixer (6) through the one-way valve (5); the hot side outlet air of the secondary radiator (3) and the cold side outlet air of the primary radiator (2) are fully mixed in the mixer (6) to meet the requirement of air supply temperature of the cabin, and are supplied to the cabin to realize heating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111168580.1A CN113830311B (en) | 2021-09-30 | 2021-09-30 | Device and method for adjusting air supply temperature of general aircraft cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111168580.1A CN113830311B (en) | 2021-09-30 | 2021-09-30 | Device and method for adjusting air supply temperature of general aircraft cabin |
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| Publication Number | Publication Date |
|---|---|
| CN113830311A true CN113830311A (en) | 2021-12-24 |
| CN113830311B CN113830311B (en) | 2023-07-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111168580.1A Active CN113830311B (en) | 2021-09-30 | 2021-09-30 | Device and method for adjusting air supply temperature of general aircraft cabin |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262495A (en) * | 1979-09-20 | 1981-04-21 | The Boeing Company | Cabin-air recirculation system powered by cabin-to-ambient pressure differential |
| CN105620761A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Temperature and humidity integrated control device of small cabin |
| CN107521697A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite type equipment cooling device |
| CN107521700A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite type cabin air recirculating system |
| CN207482197U (en) * | 2017-10-25 | 2018-06-12 | 新乡航空工业(集团)有限公司 | A kind of cockpit heating system for recycling engine tail gas heat quantity |
| CN209634735U (en) * | 2018-11-05 | 2019-11-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane synthetic formula refrigerating plant |
-
2021
- 2021-09-30 CN CN202111168580.1A patent/CN113830311B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262495A (en) * | 1979-09-20 | 1981-04-21 | The Boeing Company | Cabin-air recirculation system powered by cabin-to-ambient pressure differential |
| CN105620761A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Temperature and humidity integrated control device of small cabin |
| CN107521697A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite type equipment cooling device |
| CN107521700A (en) * | 2017-07-28 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite type cabin air recirculating system |
| CN207482197U (en) * | 2017-10-25 | 2018-06-12 | 新乡航空工业(集团)有限公司 | A kind of cockpit heating system for recycling engine tail gas heat quantity |
| CN209634735U (en) * | 2018-11-05 | 2019-11-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airplane synthetic formula refrigerating plant |
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| CN113830311B (en) | 2023-07-21 |
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