Constant-volume combustion (CVC) chamber for an aircraft turbine engine including an intake/exhaust valve having a spherical plug

Patent metadata

Field	Value
Publication number	US-11066991-B2
Application number	US-201816235992-A
Country	US
Kind code	B2
Filing date	Dec 28, 2018
Priority date	Aug 3, 2012
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

A constant-volume combustion chamber for an aircraft turbine engine, including a compressed gas intake valve configured to adopt an open position and a closed position, and in the closed position blocking intake of compressed gas into the chamber, and a combusted gas exhaust valve configured to adopt a closed position, in the closed position blocking exhaust of combusted gas outside the chamber. At least one of the intake and exhaust valves includes at least one spherical plug.

First claim

The invention claimed is:

1. A constant-volume combustion chamber for an aircraft turbine engine, the combustion chamber comprising:
a compressed gas intake valve configured to adopt an open position and a closed position, in the closed position blocking intake of compressed gas into the combustion chamber; and
a combusted gas exhaust valve configured to adopt an open position and a closed position, in the closed position blocking exhaust of combusted gas outside the combustion chamber;
wherein at least one of the compressed gas intake valve and the combusted gas exhaust valve comprises a spherical plug including an inner spherical body including two mutually distant orifices traversed by a gas passage,
wherein the combusted gas exhaust valve includes a fixed body forming a seat for the inner spherical body of the spherical plug, in the open position the two mutually distant orifices of the inner spherical body align with a respective two mutually distant orifices of the fixed body to allow exhaust of combusted gas outside the combustion chamber, the fixed body further including a body passage passing through the fixed body,
wherein the combustion chamber further comprises a conduit connected to the body passage and to a sidewall of another combustion chamber, and
wherein the inner spherical body of the spherical plug of the combusted gas exhaust valve is rotated to the closed position in which the gas passage communicates with the body passage to enable the combusted gases trapped in the gas passage to be injected through the body passage towards the another combustion chamber via the conduit.

Assignees

• Safran Aircraft Engines

Inventors

• Robic Bernard

Classifications

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F23R7/00

  Intermittent or explosive combustion chambers · CPC title

• Y10T137/8803

  Also carries head of other valve · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• Y10T137/88022

  One valve head provides seat for other head · CPC title