Combustor chamber arrangement with sealing ring

Patent metadata

Field	Value
Publication number	US-10907830-B2
Application number	US-201816187022-A
Country	US
Kind code	B2
Filing date	Nov 12, 2018
Priority date	Dec 5, 2017
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A combustion chamber arrangement comprises an annular combustion chamber, a plurality of circumferentially arranged vanes and a radially inner sealing ring. The vanes are arranged at the axially downstream end of the annular combustion chamber. Each of the vanes comprises an aerofoil extending radially between a radially inner platform and a radially outer platform. The radially inner sealing ring forms a seal between a downstream end of a radially inner annular wall structure of the combustion chamber and the radially inner platforms of the vanes. A portion of the axial length of the radially inner sealing ring comprises a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define a chamber. The radially inner wall has apertures to supply coolant into the chamber and the radially outer wall has effusion cooling apertures to supply coolant onto the surface of the radially outer wall.

First claim

The invention claimed is:

1. A combustion chamber arrangement comprising an annular combustion chamber, a plurality of circumferentially arranged vanes, a radially inner sealing ring and a radially outer sealing ring,
the annular combustion chamber comprising a radially inner annular wall structure, a radially outer annular wall structure spaced radially outwardly from the radially inner annular wall structure and an axially upstream annular wall structure, an upstream end of the radially inner annular wall structure being secured to a radially inner end of the axially upstream annular wall structure and an upstream end of the radially outer annular wall structure being secured to a radially outer end of the axially upstream annular wall structure,
the vanes being arranged at the axially downstream end of the annular combustion chamber, each of the vanes comprising a radially inner platform, a radially outer platform and an aerofoil extending radially between the radially inner platform and the radially outer platform,
the radially inner sealing ring being arranged to form a seal between a downstream end of the radially inner annular wall structure and the radially inner platforms of the vanes and the radially outer sealing ring being arranged to form a seal between a downstream end of the radially outer annular wall structure and the radially outer platforms of the vanes,
at least a portion of the axial length of the radially inner sealing ring comprising a dual wall structure, the dual wall structure including a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define at least one chamber, the radially inner wall having a plurality of apertures to supply coolant into the at least one chamber and the radially outer wall having a radially outer surface and a plurality of effusion cooling apertures to supply coolant from the at least one chamber onto the radially outer surface of the radially outer wall,
wherein an upstream end of the radially inner sealing ring having an annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the radially inner sealing ring having an annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes.

2. A combustion chamber arrangement as claimed in claim 1 wherein the radially inner wall and the radially outer wall are parallel.

3. A combustion chamber arrangement as claimed in claim 1 , wherein the downstream end of the radially inner sealing ring being at a greater radius than the upstream end of the radially inner sealing ring.

4. A combustion chamber arrangement as claimed in claim 1 , wherein the dual wall structure extends the full axial length of the radially inner sealing ring.

5. A combustion chamber arrangement as claimed in claim 1 , wherein the radially inner wall of the dual wall structure comprising a ring and the radially outer wall comprising a plurality of circumferentially arranged tiles secured on the ring.

6. A combustion chamber arrangement as claimed in claim 5 , wherein the tiles extend the full length of the radially inner wall of the dual wall structure.

7. A combustion chamber arrangement as claimed in claim 5 , wherein each tile is secured to the ring by at least one fastener arrangement.

8. A combustion chamber arrangement comprising an annular combustion chamber, a plurality of circumferentially arranged vanes, a radially inner sealing ring and a radially outer sealing ring,
the annular combustion chamber comprising a radially inner annular wall structure, a radially outer annular wall structure spaced radially outwardly from the radially inner annular wall structure and an axially upstream annular wall structure, an upstream end of the radially inner annular wall structure being secured to a radially inner end of the axially upstream annular wall structure and an upstream end of the radially outer annular wall structure being secured to a radially outer end of the axially upstream annular wall structure,
the vanes being arranged at the axially downstream end of the annular combustion chamber, each of the vanes comprising a radially inner platform, a radially outer platform and an aerofoil extending radially between the radially inner platform and the radially outer platform,
the radially inner sealing ring being arranged to form a seal between a downstream end of the radially inner annular wall structure and the radially inner platforms of the vanes and the radially outer sealing ring being arranged to form a seal between a downstream end of the radially outer annular wall structure and the radially outer platforms of the vanes,
at least a portion of the axial length of the radially inner sealing ring comprising a dual wall structure, the dual wall structure including a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define at least one chamber, the radially inner wall having a plurality of apertures to supply coolant into the at least one chamber and the radially outer wall having a radially outer surface and a plurality of effusion cooling apertures to supply coolant from the at least one chamber onto the radially outer surface of the radially outer wall,
wherein the radially outer wall of the dual wall structure comprises a ring and the radially inner wall comprises at least one member secured on the ring.

9. A combustion chamber arrangement as claimed in claim 8 , wherein an upstream end of the radially outer wall of the dual wall structure has an annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the radially outer wall of the dual wall structure has an annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes.

10. A combustion chamber arrangement as claimed in claim 9 , wherein an upstream end of the at least one member is secured to a structure defining the annular circumferentially and axially extending slot and a downstream end of the at least one member is secured to a structure defining the annular circumferentially and radially extending slot to define a single chamber.

11. A combustion chamber arrangement as claimed in claim 8 , wherein a plurality of members are secured to the ring to define a plurality of chambers and at least one of the members has apertures to supply coolant into one of the chambers.

12. A combustion chamber arrangement as claimed in claim 1 , wherein the radially outer wall and the radially inner wall of the dual wall structure are an integral structure, a single piece, a unitary piece or a monolithic piece.

13. A combustion chamber arrangement comprising an annular combustion chamber, a plurality of circumferentially arranged vanes, a radially inner sealing ring and a radially outer sealing ring,
the annular combustion chamber comprising a radially inner annular wall structure, a radially outer annular wall structure spaced radially outwardly from the radially inner annular wall structure and an axially upstream annular wall structure, an upstream end of the radially inner annular wall structure being secured to a radially inner end of the axially upstream annular wall structure and an upstream end of the radially outer annular wall structure being secured to a radially outer end of t

Assignees

• Rolls Royce Plc

Inventors

• Wilson David P
• Rimmer John E
• Martin Damian

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F02C7/18

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