Annular combustor for a gas turbine engine

Abstract

A segmented annular combustor for a gas turbine engine, axially extending between a first axial burner end and a second axial outlet end and radially extending between an annular inner liner and an annular outer liner, wherein the annular combustor is at least an assembly of: a first part including the annular inner liner and a first connection element for connecting the first part to the gas turbine engine, a second part including the annular outer liner and a second connection element for connecting the second part to the gas turbine engine independently from the first part, the second part being attachable to the first part in a removable way, at least one of the first connection element and of the second connection element being adjacent to the outlet end of the combustor.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This application is the US National Stage of International Application No. PCT / EP2016 / 056793 filed Mar 29, 2016, and claims the benefit thereof. The International Application claims the benefit of European Application No. EP15162999 filed Apr 9, 2015. All of the applications are incorporated by reference herein in their entirety.FIELD OF INVENTION[0002]The present invention relates to an annular combustor for a gas turbine engine and to a gas turbine engine including such a combustor.ART BACKGROUND[0003]Annular combustors are well known in the field of gas turbine engines.[0004]An annular combustor is normally included in a gas turbine engine 1 comprising, arranged in flow series: a compressor section, a burner, the annular combustor and a gas turbine section. In operation of the gas turbine engine, air is compressed by the compressor section and delivered to the combustion section, including the burner and the annular combustor. The comp...

AI Technical Summary

Benefits of technology

The present invention provides an annular combustor for a gas turbine engine, which reduces or eliminates the gap between the combustor and the inlet of the turbine section, thus minimizing hot gas ingestion and resulting in a more robust design. The segmentation of the combustor allows for easier and cheaper repair and replacement of certain parts on site. The reduced gap also improves flow path aerodynamics and avoids leakages through the contacts between the parts of the annular combustor.

Problems solved by technology

This leads to damages to the components, due to hot gas ingestion, i.e. the hot gas exiting the second axial outlet end of the combustor and leaking through the gap between combustor and gas turbine section;—when a reparation is required, repairing an annular combustor like the one described above, i.e. a combustor manufactured in a unitary piece attached to the casing of the gas turbine engine, is expensive.

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