US2018149365A1PendingUtilityA1

Turbine engine cvc combustion chamber module comprising a pre-combustion chamber

Assignee: SAFRAN HELICOPTER ENGINESPriority: Jun 11, 2015Filed: Jun 9, 2016Published: May 31, 2018
Est. expiryJun 11, 2035(~8.8 yrs left)· nominal 20-yr term from priority
F23R 3/28F02C 5/12F02C 5/02F23N 2227/40F23C 13/06F23C 2900/03002F23R 7/00F23R 3/40F23R 3/42F05D 2240/35F23C 13/00
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Claims

Abstract

A turbine engine combustion chamber module including at least one constant-volume combustion chamber. The module includes, upstream of the at least one constant-volume combustion chamber, a precombustion chamber capable of producing hot combustion gases that supply the at least one constant-volume combustion chamber so as to allow the ignition thereof.

Claims

exact text as granted — not AI-modified
1 - 7 . (canceled) 
     
     
         8 . A turbomachine combustion chamber module, comprising:
 a plurality of constant-volume combustion type combustion chambers distributed about an axis of rotation of the turbomachine,   upstream of said plurality of constant-volume combustion type combustion chambers, a pre-combustion chamber capable of producing hot combustion gases supplying said plurality of constant-volume combustion type combustion chamber to allow the ignition thereof,   wherein the pre-combustion chamber supplies hot combustion gases to the constant-volume combustion type combustion chambers through a rotary distributor type system.   
     
     
         9 . The module according to  claim 8 , wherein the pre-combustion chamber is of the constant-pressure combustion type. 
     
     
         10 . The module according to  claim 8 , wherein the pre-combustion chamber is configured to produce predominantly burnt gases of carbon monoxide and dihydrogen. 
     
     
         11 . The module according to  claim 8 , further comprising, downstream of the pre-combustion chamber and upstream of said plurality of constant-volume combustion type combustion chambers, an oxidation catalyst module, so to increase the dihydrogen rate of the hot combustion gases supplying said plurality of constant-volume combustion type combustion chambers to allow the ignition thereof. 
     
     
         12 . A turbomachine, including a combustion chamber module according to  claim 8 .

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