Ventilation of a turbomachine nacelle

Patent metadata

Field	Value
Publication number	US-2016138472-A1
Application number	US-201414898980-A
Country	US
Kind code	A1
Filing date	Jun 13, 2014
Priority date	Jun 18, 2013
Publication date	May 19, 2016
Grant date	—

Abstract

The invention relates to a jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, said two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R 2 is centred on the axis of a nozzle, the centre-to-centre distance nozzles being substantially equal to π/2 times R 2 or (π/2)R 2.

First claim

1 . Ejector of the jet pump type for a turbine engine, comprising a duct configured for the passage of a secondary ventilation air flow, a first end of which forms an air input and a second end of which forms an air output wherein two nozzles configured for spraying a primary air flow are mounted in the duct which defines a mixer and a diffuser downstream of the nozzle, said two nozzles being parallel and next to one another, and wherein the mixer comprises two substantially planar longitudinal walls, lower and upper respectively, which are interconnected by two side walls having a semi-circular cross section and the bending radius R 2 of which is centred on the axis of a nozzle, the centre-to-centre distance of the nozzles being substantially equal to (π/2)×R 2 .

2 . Ejector according to claim 1 which has a length of between 10R 2 and 16R 2 .

3 . Ejector according to claim 1 , wherein the longitudinal walls are substantially parallel and have substantially the same dimensions.

4 . Ventilation or pressurisation system for a turbine engine which comprises at least one ejector according to claim 1 .

5 . Turbine engine nacelle which comprises at least one ejector according to claim 1 .

6 . Nacelle according to claim 5 , wherein said first end of the duct forms an air input which is located in the nacelle.

7 . Nacelle according to claim 5 , wherein the second end of the duct opens onto an outer surface of the nacelle which is suitable for expelling the air leaving the duct to the outside of the turbine engine.

8 . Nacelle according to claim 5 , which comprises an annular array of ejectors which are regularly distributed around the longitudinal axis of the nacelle.

9 . Turbine engine which comprises a nacelle according to claim 5 , the spray nozzles being supplied with compressed air which is bled from a compressor of the turbine engine.

10 . Turbine engine according to claim 9 , which is a turboprop engine having two unducted and contra-rotating propellers.

Assignees

• Snecma

Inventors

• Chartier Sarah
• Duffet Jean-Christophe

Classifications

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F04F5/466

  with a plurality of nozzles arranged in parallel · CPC title

• B64D33/08 Primary

  of power plant cooling systems · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title