Constant-volume combustion module for a turbine engine, comprising communication-based ignition

Patent metadata

Field	Value
Publication number	US-11066990-B2
Application number	US-201615545287-A
Country	US
Kind code	B2
Filing date	Jan 26, 2016
Priority date	Jan 26, 2015
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

The invention relates to a turbine engine combustion module ( 10 ), in particular for an aircraft turbine engine, designed to carry out constant-volume combustion, comprising: at least two combustion chambers ( 12 A, 12 B) arranged about an axis, each chamber ( 12 A, 12 B, 12 C) comprising a compressed gas intake port ( 16 ) and a burnt gas exhaust port ( 18 ); and an ignition means that triggers combustion in the combustion chambers ( 12 A, 12 B, 12 C). The module ( 10 ) comprises at least one duct ( 80 ) which establishes a communication between a first combustion chamber ( 12 A) and at least one second combustion chamber ( 12 B) in order to inject burnt gases from the first combustion chamber ( 12 A) into the second combustion chamber ( 12 B) so as to trigger combustion in the second combustion chamber ( 12 B).

First claim

The invention claimed is:

1. A combustion module of a turbine engine, configured to implement constant-volume combustion, having at least two combustion chambers, each chamber comprising an intake port for compressed gas and an exhaust port for burnt gas, said intake ports and exhaust ports of the at least two combustion chambers being opened or closed by common respective intake/exhaust valves and an ignition means that triggers combustion in the combustion chamber,
the chambers being arranged around an axis, the module having at least one duct that can put a first combustion chamber into communication with at least one second combustion chamber in order to inject burnt gases from the first combustion chamber into said at least one second combustion chamber so as to trigger combustion in said at least one second combustion chamber,
wherein the combustion module has an obturator for opening/closing the at least one duct capable of selectively allowing burnt gases to pass from the first combustion chamber to said second combustion chamber, wherein the intake/exhaust ports of the combustion chambers are configured so that the intake/exhaust ports are opened or closed by common respective intake/exhaust valves that are synchronised and fitted rotatably around said axis, said valves cooperating with a radial opening that is formed in a wall shaped as a cylinder portion of the combustion chamber turned towards the axis, each corresponding rotary intake or exhaust valve having a tubular element, of a diameter corresponding to said cylinder portion fitted rotatably coaxially with said cylinder portion, said tubular element having a bore allowing the intake/exhaust gases to be routed, and at least one radial slot, arranged substantially in an axial plane of the radial opening of said port, and which is able to obturate or free said radial opening during the rotation of said tubular element and in that at least one of the rotary valves has on a periphery of said at least one of the rotary valves a throat portion that extends over a predetermined angular sector of the periphery of the rotary valve, said throat portion determining the at least one duct that is intended to put into communication the first combustion chamber and the at least one second combustion chamber adjacent to said first chamber, in an angular position of said rotary valve corresponding to an end of combustion in the first chamber prior to a discharge of the burnt gases and an end of filling of the second chamber prior to combustion, the rotary valve forming the obturator depending on its angular position.

2. The combustion module according to claim 1 , wherein the combustion module has at least one group of combustion chambers arranged angularly in a regular manner around said axis, said group having at least one ignition circuit dedicated to said group that employs the at least one duct which are each arranged between two chambers of said group and which can inject burnt gases from a first of the two chambers into the second of the two chambers in order to trigger combustion in said second combustion chamber.

3. The combustion module according to claim 1 , wherein the throat portion is formed in the periphery of the tubular element of the rotary exhaust valve.

4. The combustion module according to claim 1 , wherein the combustion module has a common rotary element that has the rotary intake/exhaust valves connected to one another in rotation.

5. A turbine engine having a compressor module with at least one compressor, the combustion module according to claim 1 , and a turbine module with at least one turbine, the compressor module being connected to the turbine module by a shaft, wherein the compressor module supplies the combustion module by means of a single intake duct and in that the combustion module supplies the turbine module by means of a single exhaust duct.

6. The turbine engine according to claim 5 , wherein the combustion module has a common rotary element that has the rotary intake/exhaust valves connected to one another in rotation, and at least one shaft system forms a means for driving the common rotary element connecting the rotary intake/exhaust valves to one another in rotation.

7. The method for controlling the combustion module of the turbine engine according to claim 5 , having at least one step of successive ignition of the first and the at least one second combustion chamber each of which operates successively in accordance with a cycle having:
a first phase during which the intake and exhaust ports are closed, with a first sub-phase of containment of a fresh combustible mixture then a second sub-phase of combustion of said combustible mixture in each corresponding chamber;
a second phase during which the intake port is closed and the exhaust port is open, to cause the burnt gases to be discharged from each corresponding chamber; then
a third phase during which the intake and exhaust ports are open, to cause the burnt gases to be swept with fresh gases through each corresponding chamber;
wherein, during the step of successive ignition, the intake and the exhaust gas discharge of the first chamber and the at least one second chamber are dephased so that the first chamber can be subjected to the second sub-phase while the at least one second chamber is subjected to the first sub-phase, and wherein the step of successive ignition has a sub-step of control, taking place when the first chamber is subjected to the second sub-phase, during which the first chamber and the at least one second chamber are put into communication in order to trigger combustion in the at least one second chamber.

Assignees

• Safran

Inventors

• Leyko Matthieu

Classifications

• F23R3/48

  Flame tube interconnectors, e.g. cross-over tubes · CPC title

• F23R7/00

  Intermittent or explosive combustion chambers · CPC title

• F02K7/06

  with combustion chambers having valves · CPC title

• F02C5/12 Primary

  the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants · CPC title

• F02C7/264

  Ignition · CPC title