Heating system for convergent-divergent secondary nozzle

Patent metadata

Field	Value
Publication number	US-10995702-B2
Application number	US-201816105159-A
Country	US
Kind code	B2
Filing date	Aug 20, 2018
Priority date	Aug 21, 2017
Publication date	May 4, 2021
Grant date	May 4, 2021

Abstract

An assembly for a rear of a dual-flow turbomachine having a longitudinal axis includes a secondary nozzle and a heating system. The secondary nozzle is defined about the longitudinal axis and ejects a mixture of the flows coming from a secondary vein and a primary vein of the turbomachine. The secondary nozzle is of a convergent-divergent form with a neck corresponding to a minimal cross-cross-section of the secondary nozzle. The heating system is located on a portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck or upstream from the neck.

First claim

The invention claimed is:

1. An assembly for a rear of a dual-flow turbomachine having a longitudinal axis, the assembly comprising:
a secondary nozzle defined about the longitudinal axis and configured to eject a mixture of flows coming from a secondary vein and a primary vein of the turbomachine,
the secondary nozzle being of a convergent-divergent form with a neck corresponding to a minimal cross cross-section of the secondary nozzle; and
wherein the assembly comprises a heating radiator system that comprises at least one heating plate and wherein the at least one heating plate extends longitudinally on a portion of an internal circumference of the secondary nozzle from a location downstream of the neck by a distance less than or equal to 20% of a diameter of the secondary nozzle at the neck, over the neck, to a location upstream of the neck by a distance less than or equal to twice the diameter of the secondary nozzle at the neck.

2. The assembly according to claim 1 , wherein the at least one heating plate is an electric radiator.

3. The assembly according to claim 1 , further comprising:
a primary nozzle defining a portion of the primary vein, wherein the secondary nozzle defines a portion of the secondary vein; and
a lobe mixer located at a downstream end of the primary nozzle and having alternating hot lobes extending inside the secondary vein and cold lobes extending inside the primary vein.

4. The assembly according to claim 1 , wherein a surface of the heating radiator system has a heating gradient.

5. The assembly according to claim 1 , wherein the heating of the radiator system is integrated into the secondary nozzle such that an internal flow surface of the secondary nozzle is continuous so as not to disrupt the mixture of flows.

6. A dual-flow turbomachine comprising the assembly according to claim 1 .

7. A dual-flow turbomachine comprising:
the assembly according to claim 1 ; and
an electric generator.

8. A dual-flow turbomachine comprising:
the assembly according to claim 1 ; and
a battery that supplies the heating radiator system.

Assignees

• Safran Aircraft Engines

Inventors

• Bodard Guillaume
• Gonzalez Jeremy Paul Francisco
• Jodet Norman Bruno Andre

Classifications

• F02K1/386 Primary

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

• F02K3/08

  with supplementary heating of the working fluid; Control thereof (control of fuel supply therefor F02C9/26) · CPC title

• F02K1/46

  Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing (F02K1/28, F02K1/36, F02K1/38 take precedence) · CPC title

• F05D2240/128

  Nozzles · CPC title

• F02K1/48

  Corrugated nozzles · CPC title