Nozzle-vane band for a gas turbine engine
AssigneeSnecma Moteurs
InventorsGregory Lafarge, Christophe Texier
Life of this patent
Estimating the term…
Abstract
A high-pressure turbine nozzle-vane band for a gas turbine engine, the band comprising an inside surface supporting at least one guide vane having a trailing edge that is directed towards a downstream end of the band, and an outside surface, opposite the inside surface, from which a flange extends radially, defining firstly, upstream from the flange, a passage for cooling-air, and secondly, downstream from the flange, a cavity, the inside surface of the band being provided, between the trailing edge of the guide vane and the downstream end of the band, with a coating forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in said cavity to be increased.
Claims12
1/ A high-pressure turbine nozzle-vane band for a gas turbine engine, the band comprising:
- an inside surface supporting at least one guide vane having a trailing edge that is directed towards a downstream end of the band;
- and
- an outside surface, opposite the inside surface, from which a flange extends radially, defining firstly, upstream from the flange, a passage for cooling-air, and secondly, downstream from the flange, a cavity,
- wherein the inside surface of the band is provided, between the trailing edge of the guide vane and the downstream end of the band, with a coating forming a thermal barrier enabling a temperature gradient generated in the band by the air spinning in said cavity to be increased.
2/ A band according to claim 1, wherein the thermal-barrier-forming coating has a surface which extends in continuity from the inside surface of the band upstream from the thermal barrier.
3/ A band according to claim 1, wherein the outside surface of the band includes spoiler projections extending between the flange and the downstream end of the band.
4/ A band according to claim 3, wherein the spoiler projections are ribs extending substantially parallel to an axis of the turbine.
5/ A band according to claim 3, wherein the spoiler projections are ribs that are substantially inclined relative to an axis of the turbine.
6/ A band according to claim 3, wherein the spoiler projections are curved ribs.
7/ A band according to claim 3, wherein the spoiler projections are studs.
8/ A band according to claim 7, wherein the studs are aligned in rows that are substantially parallel to an axis of the turbine.
9/ A band according to claim 7, wherein the studs are disposed in staggered rows.
10/ A band according to claim 1, wherein the outside surface of the band includes, upstream from the flange, at least an impact sheet so as to ensure that said band is cooled by impact.
11/ A band according to claim 1, wherein the band is pierced, upstream from the flange, by a plurality of air-passing holes designed to ensure that said band is cooled by a film of air.
12/ A high-pressure turbine nozzle for a gas turbine engine, the nozzle including at least a top band and at least a bottom band according to claim 1.