Inertial separator

Patent metadata

Field	Value
Publication number	US-10286407-B2
Application number	US-201514713119-A
Country	US
Kind code	B2
Filing date	May 15, 2015
Priority date	Nov 29, 2007
Publication date	May 14, 2019
Grant date	May 14, 2019

Abstract

An inertial separator for removing particles from a fluid stream includes a body defining a through passage, with at least one separator inlet and at least one separator outlet, a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage.

First claim

What is claimed is:

1. A gas turbine engine having an inertial separator for removing particles from a fluid stream, comprising: a gas turbine engine; and an inertial separator, the inertial separator comprising: a body defining a through passage, with at least one separator inlet and at least one separator outlet, the separator outlet being connected to a downstream portion of the gas turbine engine having a temperature higher than a temperature of the fluid stream passing through the inertial separator during operation of the gas turbine engine; a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and defining an inside and an outside for the through passage; and a flow splitter provided fluidly downstream of the turn and having at least one particle outlet fluidly coupled to the outside of the through passage; wherein the turn is configured to concentrate particles entrained in the fluid stream and confine the particles within the body until the fluid stream encounters the flow splitter; wherein the flow splitter is configured to divide the fluid stream into a reduced particle stream that exits through the at least one separator outlet and a concentrated particle stream passing through the at least one particle outlet; wherein the body further comprises a winding portion defining the turn; wherein the winding portion effects at least a 360 degree change of direction of the fluid stream; wherein the body has a transition portion between the turn and one of the at least one separator inlet and the at least one separator outlet, with the transition portion having a change in cross-sectional area; and wherein the winding portion defines a centerline for the through passage following a space curve.

2. The gas turbine engine according to claim 1 , wherein the turn effects at least a 45 degree change of direction of the fluid stream.

3. The gas turbine engine according to claim 2 , wherein the turn effects at least a 360 degree change of direction of the fluid stream.

4. The gas turbine engine according to claim 1 , wherein the turn comprises one continuous portion of the body.

5. The gas turbine engine according to claim 1 , wherein the change in cross-sectional area comprises a decrease in the cross-sectional area in a direction from the at least one separator inlet to the at least one separator outlet.

6. The gas turbine engine according to claim 1 , wherein the body has a transition portion between the turn and one of the at least one separator inlet and the at least one separator outlet, with the transition portion having a change in cross-sectional area.

7. The gas turbine engine according to claim 6 , wherein the change in cross-sectional area comprises a decrease in the cross-sectional area in a direction from the at least one separator inlet to the at least one separator outlet.

8. The gas turbine engine according to claim 1 , wherein the turn defines a centerline for the through passage following a space curve.

9. The gas turbine engine according to claim 1 , wherein the turn comprises multiple turns.

10. The gas turbine engine according to claim 1 , wherein the at least one particle outlet comprises multiple particle outlets disposed along the outside of the through passage.

11. A gas turbine engine having an inertial separator for removing particles from a fluid stream, comprising: a gas turbine engine; and an inertial separator, the inertial separator comprising: a body defining a through passage, with at least one separator inlet and at least one separator outlet, the separator outlet being connected to a downstream portion of the gas turbine engine having a temperature higher than a temperature of the fluid stream passing through the separator during operation of the gas turbine engine; a winding turn provided in the body between the at least one separator inlet and the at least one separator outlet, and defining an inside and outside for the through passage; and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage, downstream of the winding turn; wherein the winding turn defines for the through passage a centerline following a space curve and effects at least a 360 degree change of direction of the fluid stream; and wherein the body has a transition portion between the winding turn and one of the at least one separator inlet and the at least one separator outlet, with the transition portion having a change in cross-sectional area.

12. The gas turbine engine according to claim 11 , wherein the change in cross-sectional area comprises a decrease in the cross-sectional area in a direction from the at least one separator inlet to the at least one separator outlet.

13. The gas turbine engine according to claim 11 , wherein an orthogonal projection from a plane defining the at least one separator inlet defines an inlet axis and an orthogonal projection from a plane defining the at least one separator outlet defines an outlet axis, wherein the inlet axis and the outlet axis are not coaxial.

14. The gas turbine engine according to claim 11 , wherein the at least one particle outlet comprises multiple particle outlets disposed along the outside of the through passage.

Assignees

• Gen Electric

Inventors

• Correia Victor Hugo Silva
• Manning Robert Francis
• Buhler Jared Peter

Classifications

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• B01D45/16

  generated by the winding course of the gas stream {, the centrifugal forces being generated solely or partly by mechanical means, e.g. fixed swirl vanes} · CPC title

• B04C2003/003

  Shapes or dimensions of vortex chambers · CPC title

• B01D45/04

  by utilising inertia (B01D45/12 takes precedence) · CPC title