Aspirator

Patent metadata

Field	Value
Publication number	US-10676197-B2
Application number	US-201715398309-A
Country	US
Kind code	B2
Filing date	Jan 4, 2017
Priority date	Jan 4, 2017
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

An aspirator may comprise an aspirator body defining an air channel and an inlet. A flow straightener may be disposed at the inlet. The flow straightener may be configured to produce a laminar flow through the air channel. An aspirator barrel may be coupled to the aspirator body and may define an outlet. A static airfoil assembly may be disposed at the outlet. The static airfoil assembly may be configured to produce a vortex flow exiting the aspirator barrel.

First claim

What is claimed is:

1. An aspirator, comprising:
an aspirator body defining an air channel and an inlet, wherein the aspirator body is configured such that environmental gas enters the aspirator through the inlet;
a flow straightener disposed at the inlet, the flow straightener configured to produce a laminar flow through the air channel, wherein the flow straightener is configured to direct the environmental gas into the aspirator body in a direction parallel to a longitudinal axis of the aspirator;
a gas valve in fluid communication with the air channel, wherein fluid traveling through the gas valve enters the air channel downstream of the inlet;
an aspirator barrel coupled to the aspirator body and defining an outlet; and
a static airfoil assembly disposed at the outlet, the static airfoil assembly configured to produce a vortex flow exiting the aspirator barrel.

2. The aspirator of claim 1 , wherein the flow straightener comprises a body defining a plurality of apertures configured to direct the airflow.

3. The aspirator of claim 1 , wherein the flow straightener includes a honeycomb structure configured to reduce turbulence of airflow entering the air channel.

4. The aspirator of claim 1 , wherein the vortex flow exiting the aspirator barrel is directed in a spiral motion centered around the longitudinal axis of the aspirator.

5. The aspirator of claim 1 , wherein the static airfoil assembly comprises a plurality of static airfoils arranged in a spoke configuration.

6. The aspirator of claim 5 , wherein the plurality of static airfoils have an arcuate cross-sectional shape and are stationary with respect to the aspirator barrel.

7. An evacuation system for use with an aircraft, comprising:
an inflatable evacuation device configured to be inflated by a compressed fluid source; and
an aspirator coupled to the compressed fluid source and to the inflatable evacuation device, the aspirator comprising:
an aspirator body defining an air channel and an inlet, wherein the aspirator is configured such that environmental gas enters the air channel through the inlet, and
a flow straightener disposed at the inlet, the flow straightener configured to produce a laminar flow through the air channel, wherein the flow straightener comprises a body defining a plurality of apertures configured to direct the environmental gas in a direction parallel to a longitudinal axis of the aspirator.

8. The evacuation system of claim 7 , wherein the flow straightener includes a honeycomb structure configured to reduce turbulence of airflow entering the air channel.

9. The evacuation system of claim 7 , further comprising an aspirator barrel coupled to the aspirator body and defining an outlet; and
a static airfoil assembly disposed at the outlet, the static airfoil assembly configured to produce a vortex flow exiting the aspirator barrel.

10. The evacuation system of claim 9 , wherein the static airfoil assembly comprises a plurality of static airfoils arranged in a spoke configuration.

11. The evacuation system of claim 9 , wherein the aspirator comprises a longitudinal axis, and wherein the vortex flow exiting the aspirator barrel is directed in a spiral motion centered around the longitudinal axis of the aspirator.

12. The evacuation system of claim 7 , wherein the aspirator is configured to pack with the inflatable evacuation device within the aircraft.

13. An aspirator method, comprising;
disposing a flow straightener at an inlet of an aspirator, the aspirator including a gas valve downstream of the inlet;
aspirating air through the flow straightener into an air channel defined by the aspirator, the flow straightener producing a laminar flow through the air channel; and
disposing a static airfoil assembly at an outlet of the aspirator, the static airfoil assembly producing a vortex flow exiting the aspirator.

14. The aspirator method of claim 13 , wherein the aspirator comprises a longitudinal axis, and wherein the flow straightener directs an airflow into the air channel in a direction parallel to the longitudinal axis of the aspirator.

15. The aspirator method of claim 13 , wherein the flow straightener includes a honeycomb structure configured to reduce turbulence of airflow entering the air channel.

16. The aspirator method of claim 13 , wherein the aspirator comprises a longitudinal axis, and wherein the vortex flow exiting the outlet is directed in a spiral motion centered around the longitudinal axis of the aspirator.

17. The aspirator method of claim 13 , further comprising directing the vortex flow from the aspirator into an inflatable evacuation device.

Assignees

• Goodrich Corp

Inventors

• Haynes Timothy C
• Bahena Daniel

Classifications

• F04F5/46

  Arrangements of nozzles · CPC title

• F04F5/18

  for compressing · CPC title

• B64D25/18

  Flotation gear · CPC title

• F04F5/16

  displacing elastic fluids · CPC title

• F04F5/463

  with provisions for mixing · CPC title