The present invention relates to a system for the preparation of air in an aircraft comprising a compressor charged with air on the inlet side, comprising a supply air heat exchanger which is downstream of the compressor, is charged with air compressed in the compressor on the pressurized air side o
The present invention relates to a system for the preparation of air in an aircraft comprising a compressor charged with air on the inlet side, comprising a supply air heat exchanger which is downstream of the compressor, is charged with air compressed in the compressor on the pressurized air side on the inlet side and which is in communication on the pressurized air side on the outlet side with a system or unit which is to be supplied with pressurized air, and comprising a turbine which is charged on the inlet side with pressurized air from a pressurized air supply separate from the air supply of the compressor and is in communication on the outlet side with the low pressure side inlet of the supply air heat exchanger and which is in communication with the compressor such that the compressor can be driven by means of the turbine. The invention furthermore relates to a method for the preparation of air in an aircraft.
대표청구항▼
The invention claimed is: 1. A system for the preparation of air in an aircraft comprising a compressor (C) charged with air on the inlet side, comprising a supply air heat exchanger (OHX) which is downstream of the compressor (C), is charged with air compressed in the compressor (C) on the pressur
The invention claimed is: 1. A system for the preparation of air in an aircraft comprising a compressor (C) charged with air on the inlet side, comprising a supply air heat exchanger (OHX) which is downstream of the compressor (C), is charged with air compressed in the compressor (C) on the pressurized air side on the inlet side and which is in communication on the pressurized air side on the outlet side with a system (OBIGGS) or unit which is to be supplied with pressurized air, and comprising a turbine (T) which is charged on the inlet side with pressurized air from a pressurized air supply separate from the air supply of the compressor (C) and is in communication on the outlet side with the low pressure side inlet of the supply air heat exchanger (OHX) and which is in communication with the compressor (C) such that the compressor (C) can be driven by the turbine (T), wherein a pressurized air heat exchanger (THX) is disposed upstream of the turbine (T). 2. A system in accordance with claim 1, wherein the compressor (C) is charged on the inlet side with air from a pressurized space of an aircraft, preferably with cabin exhaust air. 3. A system in accordance with claim 1, wherein the pressurized air supplied to the turbine (T) is bled air from the engines or from an auxiliary unit of the vehicle. 4. A system in accordance with claim 1, wherein the pressurized air heat exchanger (IHX) is disposed downstream of the supply air heat exchanger (OHX) on the low pressure side so that the turbine outlet air first flows through the supply air heat exchanger (OHX) and then through the pressurized air heat exchanger (THX). 5. A system in accordance with claim 1, wherein the pressurized air heat exchanger (THX) forms a mechanical unit with the supply air heat exchanger (OHX) and is separate from it on the pressurized air side. 6. A system in accordance with claim 1, wherein the supply air heat exchanger (OHX) and the pressurized air heat exchanger (IHX) are separate mechanically and on the pressurized air side. 7. A system in accordance with claim 1, wherein a bypass line is provided which can be closed by means of a valve (TBPV) and which connects the inlet of the pressurized air heat exchanger (THX) on the pressurized air side to its outlet on the pressurized air side. 8. A system in accordance with claim 1, wherein a bypass line is provided which can be closed by a valve (OBPV) and which connects the inlet of the supply air heat exchanger (OHX) on the pressurized air side to its outlet on the pressurized air side. 9. A system in accordance with claim 1, wherein the compressor is made in one or more stages; and/or one or more compressors are provided. 10. A system in accordance with claim 1, wherein a line is provided by means of which the outlet air of the heat exchangers (OHX, THX) on the low pressure side can be discharged to ambient or can be guided into a ram air passage of an aircraft air-conditioning system. 11. A system in accordance with claim 1, wherein a valve (TIV) is provided by which the air flow supplied to the turbine (T) can be changed or blocked. 12. A system in accordance with claim 1, wherein a valve (OSOV) is provided by which the air flow supplied to the compressor (C) can be changed or blocked. 13. A system in accordance with claim 1, wherein the compressor (C) and the turbine (T) form a shaft device with a common shaft. 14. A system in accordance with claim 13, wherein the shaft device has a drive motor (M) to drive the compressor (C). 15. A system in accordance with claim 13, wherein the shaft device and the heat exchangers (OHX; THX) form a common mechanical unit or are mechanically separate. 16. A method for the preparation of air in an aircraft with the system of claim 1, wherein the air is compressed in the compressor (C), the compressed air is cooled on the pressurized air side of the supply air heat exchanger (OHX) and then supplied to the system (OBIGGS) or unit which is to be supplied with pressurized air, the cooling of the air compressed in the compressor (C) takes place by the air which is supplied to the turbine (T) by the pressurized air supply separate from the air supply of the compressor (C), expanded in it and supplied to the low pressure side of the supply air heat exchanger (OHX), and the turbine performance created on the expansion being utilized at least in part to drive the compressor (C). 17. A method in accordance with claim 16, wherein cabin exhaust air is compressed in the compressor (C). 18. A method in accordance with claim 16, wherein cooled or non-cooled pressurized air is supplied to the turbine (T) from an engine or from an auxiliary unit. 19. A method in accordance with claim 16, wherein the pressurized air supplied to the turbine (T) is cooled in the pressurized air heat exchanger (THX) prior to the entry into the turbine (T). 20. A method in accordance with claim 16, wherein the turbine outlet air for the cooling of the air compressed in the compressor (C) first flows through the supply air heat exchanger (OHX) and subsequently flows through the pressurized air heat exchanger (THX) to cool the pressurized air supplied to the turbine (T). 21. A method in accordance with claim 16, wherein the outlet air of the heat exchangers on the low pressure side is discharged to ambient or is introduced into the ram air passage of an aircraft air-conditioning system. 22. A method in accordance with claim 16, wherein the compressor (C) is additionally driven by a motor on a low pressure of the pressurized air supplied to the turbine (T). 23. A method in accordance with claim 16, wherein an operating mode is provided to ensure a minimum temperature of the pressurized air supplied to the system (OBIGGS) or unit, in which operating mode air compressed in the compressor (C) is guided from the inlet side on the pressurized air side to the outlet side of the supply air heat exchanger (OHX) on the pressurized air side while at least partly bypassing the supply air heat exchanger (OHX). 24. A method in accordance with claim 16, wherein an operating mode is provided to increase the turbine inlet temperature, in which operating mode the pressurized air is guided from the inlet side on the pressurized air side to the outlet side of the pressurized air heat exchanger (THX) on the pressurized air side while at least partly bypassing the pressurized air heat exchanger (THX). 25. A method in accordance with claim 16, wherein an operating mode is provided for the limitation of the turbine inlet pressure, in which operating mode the pressurized air flow supplied to the turbine (T) is restricted. 26. A system in accordance with claim 1, wherein a hot-air side of the pressurized air heat exchanger (THX) is disposed upstream of the turbine (T). 27. A system in accordance with claim 26, wherein a cold-air side of the pressurized air heat exchanger (THX) is disposed downstream of the turbine (T).
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (7)
Veltman Joost (San Jose CA) Malik Ram L. (Fremont CA) Dickens Michael D. (Danville CA), Air purification and temperature controlling system and method.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.