Aircraft cabin air temperature sensing apparatus and system using passive air flow

Patent metadata

Field	Value
Publication number	US-2019055024-A1
Application number	US-201615765181-A
Country	US
Kind code	A1
Filing date	Oct 7, 2016
Priority date	Oct 8, 2015
Publication date	Feb 21, 2019
Grant date	—

Abstract

An air temperature sensing apparatus and a system for an aircraft includes an ejector with a first air duct for receiving a first air flow from an aircraft air distribution duct, the first air duct defining a first cross-sectional area, a second air duct for receiving a second air flow from a passenger compartment of the aircraft, the second air flow merging with the first air flow downstream of the second air duct, and a restrictor connected to the first air duct defining a minimal cross-sectional area. The apparatus and system also include a temperature sensor in fluid communication with the second air flow. The minimal cross-sectional area of the restrictor is smaller than the first cross-sectional area of the first air duct to create a region of low pressure within the ejector, causing the second air flow to be suctioned over the temperature sensor.

First claim

1 . An air temperature sensing apparatus for an aircraft, comprising:
an ejector comprising
a first air duct for receiving a first air flow from an aircraft air distribution duct, the first air duct defining a first cross-sectional area,
a second air duct for receiving a second air flow from a passenger compartment of the aircraft, the second air flow merging with the first air flow downstream of the second air duct, and
a restrictor connected to the first air duct defining a minimal cross-sectional area; and
a temperature sensor in fluid communication with the second air flow, wherein the minimal cross-sectional area of the restrictor is smaller than the first cross-sectional area of the first air duct so as to create a region of low pressure within the ejector, causing the second air flow to be suctioned over the temperature sensor and through the second air duct.

2 . The air temperature sensing apparatus of claim 1 , wherein the restrictor defines a restrictor length, the restrictor decreasing in cross-sectional area over at least a portion of the restrictor length to the minimal cross-sectional area.

3 . The air temperature sensing apparatus of claim 1 , wherein the minimal cross-sectional area is upstream of a location where the second air duct connects to the restrictor.

4 . The air temperature sensing apparatus of claim 1 , wherein the minimal cross-sectional area is at a location where the second air duct connects to the restrictor.

5 . The air temperature sensing apparatus of claim 1 , wherein the ejector further comprises:
a housing disposed around an end of the first air duct and the restrictor, wherein the second air duct connects to the housing, and wherein the minimal cross-sectional area is downstream of a location where the second air duct connects to the housing.

6 . The air temperature sensing apparatus of claim 2 , wherein the restrictor increases in cross-sectional area over at least a portion of the restrictor length downstream of the minimal cross-sectional area.

7 . The air temperature sensing apparatus of claim 1 , wherein the minimal cross-sectional area remains constant over at least a portion of the restrictor length.

8 . The air temperature sensing apparatus of claim 1 , wherein the temperature sensor is located within the second air duct.

9 . The air temperature sensing apparatus of claim 1 , further comprising:
a controller connected to the temperature sensor.

10 . The air temperature sensing apparatus of claim 1 , wherein the ejector further comprises a third air duct, connected to the restrictor.

11 . The air temperature sensing apparatus of claim 5 , further comprising a third air duct, connected to the housing.

12 . The air temperature sensing apparatus of claim 1 , further comprising:
a flow balancing device disposed in the second air duct altering the second air flow in proportion to the first air flow.

13 . The air temperature sensing apparatus of claim 12 , further comprising:
a piccolo extending from the first air duct to the flow balancing device, altering the second air flow in response to a pressure of the first air flow.

14 . A system for sensing air temperature within an aircraft, comprising:
an air distributor; an ejector comprising
a first air duct for receiving a first air flow from an aircraft air distribution duct, the first air duct defining a first cross-sectional area,
a second air duct for receiving a second air flow from a passenger compartment of the aircraft, the second air flow merging with the first air flow downstream of the second air duct, and
a restrictor connected to the first air duct defining a minimal cross-sectional area;
a temperature sensor in fluid communication with the second air flow; and
a controller connected to the temperature sensor to receive temperature information from the temperature sensor, wherein the minimal cross-sectional area of the restrictor is smaller than the first cross-sectional area of the first air duct so as to create a region of low pressure within the ejector, causing the second air flow to be suctioned over the temperature sensor and through the second air duct.

15 . The system of claim 14 , wherein the restrictor defines a restrictor length, the restrictor decreasing in cross-sectional area over at least a portion of the restrictor length to the minimal cross-sectional area.

16 . The system of claim 14 , wherein the restrictor increases in cross-sectional area over at least a portion of the restrictor length downstream of the minimal cross-sectional area.

17 . The system of claim 14 , wherein the minimal cross-sectional area remains constant over at least a portion of the restrictor length.

18 . The system of claim 14 , wherein the minimal cross-sectional area is upstream of a location where the second air duct connects to the restrictor.

19 . The system of claim 14 , wherein the minimal cross-sectional area is at a location where the second air duct connects to the restrictor.

20 . The system of claim 14 , wherein the ejector further comprises:
a housing disposed around an end of the first air duct and the restrictor, wherein the second air duct connects to the housing, and wherein the minimal cross-sectional area is downstream of a location where the second air duct connects to the housing.

21 . The system of claim 14 , wherein the temperature sensor is located within the second air duct.

22 . The system of claim 14 , wherein the ejector further comprises a third air duct, connected to the restrictor.

23 . The system of claim 22 , further comprising a third air duct, connected to the housing.

24 . The system of claim 14 , further comprising:
a flow balancing device disposed in the second air duct altering the second air flow in proportion to the first air flow.

25 . The system of claim 24 , further comprising:
a piccolo extending from the first air duct to the flow balancing device, altering the second air flow in response to a pressure of the first air flow.

Assignees

• Bombardier Inc

Inventors

• Fagundes Sandro Afonso Silva
• Stefanini Luciano Martinez
• Wang Hongzhi

Classifications

• B64D2013/0625

  comprising means for distribution effusion of conditioned air in the cabin · CPC title

• G01K1/26

  Compensating for effects of pressure changes · CPC title

• G01K13/02

  for measuring temperature of moving fluids or granular materials capable of flow · CPC title

• G01K2201/02

  in vehicles · CPC title

• B64D13/06 Primary

  the air being conditioned (pressurising B64D13/02) · CPC title