초록 ▼

The present invention relates to an evaporator arrangement for an air conditioning system of an aircraft, wherein a bypass conduit is provided which can be connected such that if required at least part of the airflow bypasses an evaporator. Advantageously this makes it possible in the case of malfun

The present invention relates to an evaporator arrangement for an air conditioning system of an aircraft, wherein a bypass conduit is provided which can be connected such that if required at least part of the airflow bypasses an evaporator. Advantageously this makes it possible in the case of malfunction of the evaporator to maintain the functionality of the air conditioning system.

대표청구항 ▼

What is claimed is: 1. An evaporator arrangement for an air conditioning system of an aircraft, comprising: a main air conduit with an evaporator arranged in the main air conduit such that an airflow in the main air conduit flows through the evaporator; a bypass air conduit connected to the main ai

What is claimed is: 1. An evaporator arrangement for an air conditioning system of an aircraft, comprising: a main air conduit with an evaporator arranged in the main air conduit such that an airflow in the main air conduit flows through the evaporator; a bypass air conduit connected to the main air conduit such that at least a part of the airflow bypasses the evaporator; and a safety valve arranged between the main air conduit and the bypass air conduit such that if a threshold pressure in the main air conduit upstream of the evaporator is exceeded, at least part of the airflow is fed to the bypass conduit through the safety valve. 2. The evaporator arrangement of claim 1, further comprising: a diffuser provided in the main air conduit upstream of the evaporator; the diffuser being operable to form the airflow in such a way that the airflow comprises airflow lines of essentially identical speed. 3. The evaporator arrangement of claim 2, further comprising: a grille provided between the diffuser and the evaporator and operable to further adjust the speed of the airflow lines. 4. The evaporator arrangement of claim 1, further comprising: a temperature sensor arranged in a first flow direction of the airflow in the main air conduit upstream of the evaporator. 5. The evaporator arrangement of claim 1, wherein the evaporator is operable so that the airflow in the evaporator has a second airflow direction, and the airflow in the evaporator has a third airflow direction when the airflow impinges on the evaporator, the second airflow direction being not orthogonal in relation to the third airflow direction. 6. The evaporator arrangement of claim 5, further comprising a flow direction device including a honeycomb structure; the flow direction device being arranged on the evaporator in the third airflow direction to deflect flow lines of the airflow and feed them to the evaporator. 7. The evaporator arrangement of claim 1, further comprising: a sound absorbent housing encasing the evaporator arrangement. 8. The evaporator arrangement of claim 1, wherein the evaporator is a direct evaporator comprising an absorbent porous, inorganic material. 9. An air conditioning system for an aircraft, comprising: an evaporator arrangement of claim 1. 10. An evaporator pad for a direct evaporator of an air conditioning system of an aircraft, the air conditioning system having a main air conduit and a bypass conduit and the direct evaporator being positioned within the main air conduit, the evaporator pad comprising: an absorbent element with a flow-through direction, the absorbent element being arranged in the direct evaporator such that the airflow in the main air conduit flows through the absorbent element if the bypass conduit is not connected at least part of the airflow bypasses the absorbent element if the bypass conduit is connected; and a flow direction device including a honeycomb structure operative for reflecting flow lines of the air flow into the evaporator. 11. The evaporator pad of claim 10, wherein the flow direction device is arranged on the absorbent element in the flow-through direction, the flow-through direction being not orthogonal to an airflow direction of an airflow impinging on the absorbent element. 12. A method for operating an evaporator arrangement of an air conditioning system of an aircraft, wherein the evaporator arrangement includes a main air conduit, a bypass air conduit, an evaporator, and a safety valve arranged between the main air conduit and the bypass air conduit, the method comprising: operating the evaporator in the main air channel such that an airflow in the main air conduit flows through the evaporator; connecting the bypass conduit so that at least part of the airflow bypasses the evaporator; and feeding at least part of the airflow to the bypass conduit through the safety valve if a threshold pressure in the main air conduit upstream of the evaporator is exceeded. 13. The method of claim 12, further comprising the step of: measuring a temperature of the airflow upstream of the evaporator; wherein the temperature is used for temperature control in the air conditioning system.