External turning vane for IFS-mounted secondary flow systems

Patent metadata

Field	Value
Publication number	US-11022047-B2
Application number	US-201916534150-A
Country	US
Kind code	B2
Filing date	Aug 7, 2019
Priority date	Aug 7, 2019
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

An external turning vane includes a vane body extending radially from the inner cowl and disposed upstream from an inlet of the secondary flow system, the vane body configured to turn an airflow in a bypass flow path towards an axial direction to minimize separation between the airflow and the secondary flow system.

First claim

What is claimed is:

1. A secondary flow system for a gas turbine engine having an inner cowl, the secondary flow system comprising:
an inlet disposed on the inner cowl, the inlet in fluid communication with a bypass flow path; and
an external turning vane disposed upstream from the inlet, the external turning vane comprising a vane body extending radially from the inner cowl, the vane body configured to turn an airflow in the bypass flow path towards an axial direction and to introduce higher momentum flow of a vortex into the inlet to minimize flow separation on a sidewall of the inlet,
wherein the external turning vane is the only external turning vane associated with the inlet for turning the airflow in the bypass flow path towards the axial direction to minimize flow separation on the sidewall of the inlet.

2. The secondary flow system of claim 1 , wherein the vane body is oriented at a non-zero angle with respect to a centerline axis of the inlet.

3. The secondary flow system of claim 1 , wherein a first height of the vane body is less than a second height of the inlet.

4. The secondary flow system of claim 3 , wherein the first height is a maximum height of the vane body and the second height is a maximum height of the inlet.

5. The secondary flow system of claim 1 , wherein the inner cowl comprises an inner fixed structure (IFS).

6. The secondary flow system of claim 1 , wherein the vane body is disposed relative to the inlet such that a wake vortex generated by the vane body during operation of the gas turbine engine is completely or nearly completely ingested by the inlet.

7. The secondary flow system of claim 1 , wherein the vane body is configured to convert kinetic energy associated with a circumferential flow direction into a vortex to introduce a higher momentum flow of the vortex into the inlet of the secondary.

8. The secondary flow system of claim 1 , wherein the vane body is configured to straighten the airflow diverted by a bifurcation of the gas turbine engine.

9. A gas turbine engine, comprising:
an outer nacelle;
an inner cowl defining a bypass flow path along with the outer nacelle for receiving fan airflow;
an inlet for a secondary flow system disposed on the inner cowl, the inlet in fluid communication with the bypass flow path; and
an external turning vane disposed upstream from the inlet, the external turning vane comprising a vane body extending radially from the inner cowl, the vane body configured to turn an airflow in the bypass flow path towards an axial direction and to introduce higher momentum flow of a vortex into the inlet to minimize flow separation on a sidewall of the inlet,
wherein the external turning vane is the only external turning vane associated with the inlet for turning the airflow in the bypass flow path towards the axial direction to minimize flow separation on the sidewall of the inlet.

10. The gas turbine engine of claim 9 , wherein the vane body is oriented at a non-zero angle with respect to a centerline axis of the inlet.

11. The gas turbine engine of claim 9 , wherein a first height of the vane body is less than a second height of the inlet.

12. The gas turbine engine of claim 9 , wherein the inner cowl comprises an inner fixed structure (IFS).

13. The gas turbine engine of claim 9 , wherein the vane body is at least one of:
disposed relative to the inlet such that a wake vortex generated by the vane body during operation of the gas turbine engine is completely or nearly completely ingested by the inlet;
configured to convert kinetic energy associated with a circumferential flow direction into a vortex to introduce a higher momentum flow of the vortex into the inlet of the secondary; and
configured to straighten the airflow diverted by a bifurcation of the gas turbine engine.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Zsurka Mark
• Carlson Laurel F

Classifications

• F02C7/045

  having provisions for noise suppression · CPC title

• F02C7/055

  with intake grids, screens or guards · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title

• F05D2220/32

  in gas turbines · CPC title