Integrated turbine exhaust struts and mixer of turbofan engine

Patent metadata

Field	Value
Publication number	US-9759159-B2
Application number	US-201414521888-A
Country	US
Kind code	B2
Filing date	Oct 23, 2014
Priority date	May 26, 2014
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.

First claim

The invention claimed is:

1. A turbine exhaust case (TEC) of a turbofan aeroengine comprising a hub and a shroud with a mixer attached to a downstream end of the shroud for mixing exhaust gases with a bypass air stream, the hub and the shroud being annular, the mixer including a plurality of axially extending lobes of the mixer arranged in alternating crests and valleys extending divergently in a downstream direction, the mixer surrounding the hub to form an annular exhaust gas duct between the mixer and the hub, a plurality of deswirling struts extending generally radially across the annular exhaust gas duct axially within the mixer to connect the mixer and the hub, the deswirling struts fewer in number than a total number of the valleys of the mixer, a selected first group of the valleys of the mixer directly connected to the deswirling struts such that the first group of valleys contact the deswirling struts at an axial location between a start point where the valleys diverge from the crests and a trailing edge of the valleys, a plurality of secondary struts having an average chord length shorter than an average chord length of the respective deswirling struts, the secondary struts generally radially extending across the annular exhaust gas duct and connected to the hub, a selected second group of the valleys distinct from the first group of the valleys directly connected to the secondary struts such that the secondary struts contact said second group of the valleys immediately upstream of a trailing edge of said valleys, the deswirling struts spaced from the selected second group of the valleys.

2. The TEC as defined in claim 1 wherein the deswirling struts comprise a cambered profile, the cambered profile being cambered in a direction of an incoming swirling flow of the exhaust gases.

3. The TEC as defined in claim 1 wherein the deswirling struts are axially spaced away from the trailing edges of the respective valleys of the selected first group of the valleys of the mixer.

4. The TEC as defined in claim 1 wherein the deswirling struts are axially located in an axial upstream half of the mixer.

5. The TEC as defined in claim 1 wherein the secondary struts comprise an airfoil profile.

6. The TEC as defined in claim 1 wherein the secondary struts comprise a flat plate.

7. The TEC as defined in claim 1 wherein a total number of the deswirling struts and the secondary struts is less than the total number of the valleys of the mixer.

8. A turbofan aeroengine comprising a turbine exhaust case (TEC) positioned downstream of a turbine section of the turbofan aeroengine for directing a flow of gases exhausted from the turbine section, the TEC including an inner annular hub surrounded by an annular outer wall, a downstream end section of the annular outer wall being in a circumferential wavy configuration to form a plurality of axially extending ions defining alternating crests and valleys extending divergently to a downstream end of the TEC, the crests defining internal axial and radially-outward passages for directing gases exiting from the turbine section to pass through the TEC, and the valleys defining external axial and radially-inward passages for directing a bypass air stream to pass along an external surface of the TEC, resulting in mixing of the oases with the bypass air stream, a number of circumferentially spaced deswirling struts having a cambered profile and being located within an axial length of the circumferential wavy configuration, the number of the deswirling struts being less than a total number of the valleys of the mixer, the deswirling struts radially interconnecting the inner annular nub and a first selected group of the valleys number of secondary struts having an average chord length shorter than the average chord length of the respective deswirling struts, the secondary struts radially interconnecting the inner annular hub and a selected second group of the valleys distinct from the first group of the valleys, the deswirling struts spaced from the selected second group of the valleys, the selected first group of the valleys of the mixer directly connected to the deswirling struts such that the first group of valleys contact the deswirling struts at an axial location between a start point where the valleys diverge from the crests and a trailing edge of the valleys, the selected second group of the valleys directly connected to the secondary struts such that secondary struts contact the second group of the valleys immediately upstream of a trailing edge of said valleys.

9. The turbofan aeroengine as defined in claim 8 wherein the deswirling struts comprise a leading edge and a trailing edge, the leading edges of the deswirling struts being axially spaced away from a start point of the divergently extending crests and valleys, and the trailing edges of the deswirling struts being axially spaced away from the trailing edges of the respective valleys of the selected first group of the valleys.

10. The turbofan aeroengine as defined in claim 8 wherein the deswirling struts and the secondary struts are circumferentially distributed such that each of the deswirling struts is positioned between adjacent two of the secondary struts.

11. The turbofan aeroengine as defined in claim 8 wherein the deswirling struts and the secondary struts are circumferentially distributed such that each of the secondary struts is positioned between adjacent two of the deswirling struts.

12. The turbofan aeroengine as defined in claim 8 wherein the deswirling struts and the secondary struts are circumferentially distributed in an alternating pattern of every one or more of the deswirling struts and every one or more of the secondary struts.

13. The turbofan aeroengine as defined in claim 8 wherein a total number of the deswirling struts and the secondary struts is equal to the total number of the valleys.

14. The turbofan aeroengine as defined in claim 8 wherein a total number of the deswirling struts and the secondary struts is less than the total number of the valleys.

15. The turbofan aeroengine as defined in claim 8 wherein the downstream end of the TEC comprises a jagged trailing edge.

16. The turbofan aeroengine as defined in claim 8 wherein the secondary struts comprise an airfoil profile.

17. The turbofan aeroengine as defined in claim 8 wherein the secondary struts comprise a flat plate.

Assignees

• Pratt & Whitney Canada

Inventors

• Marini Remo
• Cunningham Mark Huzzard

Classifications

• F02K1/386 Primary

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/61

  corrugated · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title