Stator of a high-pressure turbine of a turbomachine, and a method of assembling it

1. A method of assembling sectored elements of an annular stator of a high-pressure of a turbomachine about a longitudinal axis of said turbine, the stator comprising:

an annular casing disposed about the longitudinal axis of the high-pressure turbine;

a plurality of spacers that are sectored and mounted on the casing and onto which a plurality of ring sectors are secured, said ring sectors being disposed circumferentially about the longitudinal axis of the turbine so as to form a continuous circular surface encompassing the rotor blades of a turbine rotor; and

a plurality of angular air flow duct sectors disposed circumferentially around the casing, and designed to discharge air onto the casing in order to enable clearance at the tips of the turbine rotor blades to be tuned;

said method consisting in:

defining an angular distribution pattern for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent the inter-spacer zones defined between two adjacent spacers being in radial alignment with the duct inter-sector zones defined between two adjacent duct sectors; and in:

repeating said distribution pattern around the entire circumference of the stator.

2. A method according to claim 1 , wherein the angular distribution pattern is repeated symmetrically in rotation relative to the predetermined angular sector.

3. A method according to claim 1 , in which the stator elements further consist of a plurality of air supply inlets disposed through the casing and designed to supply air to a stage of a low-pressure distributor of the turbomachine, said stage being disposed downstream from the high-pressure turbine, said method further consisting in aligning each air supply inlet radially with a duct inter-sector zone.

4. A method according to claim 1 , wherein an angular air flow duct sector corresponds to the predetermined angular sector.

5. A method according to claim 1 , wherein three spacers and one air supply inlet are associated with each angular air flow duct sector.

6. A method according to claim 5 , wherein two ring sectors are connected to each spacer.

7. A stator of a high-pressure turbine of a turbomachine comprising the following elements:

an annular casing disposed about a longitudinal axis of the high-pressure turbine;

a plurality of spacers that are sectored and mounted on the casing and onto which a plurality of ring sectors are secured, said ring sectors being disposed circumferentially about the longitudinal axis of the high-pressure turbine so as to form a continuous circular surface encompassing the rotor blades of a high-pressure turbine rotor;

a plurality of angular air flow duct sectors disposed circumferentially around the casing and designed to discharge air onto the casing in order to enable clearance at the tips of the high-pressure turbine rotor blades to be tuned; and

a plurality of air supply inlets disposed through the casing and designed to supply air to a low-pressure distributor stage of the turbomachine, said stage being disposed downstream from the high-pressure turbine;

said stator being wherein the stator elements are distributed angularly about the longitudinal axis of the high-pressure turbine so as to prevent the inter-spacer zones defined between two adjacent spacers being in radial alignment with the duct inter-sector zones defined between two adjacent duct sectors.

8. A stator according to claim 7 , wherein the stator elements are distributed angularly about the longitudinal axis of the high-pressure turbine, so as also to cause each air supply inlet 30 to be in radial alignment with a duct inter-sector zone.

9. A stator according to claim 7 , having N angular air flow duct sectors, 3N spacers, and N air supply inlets.

10. A stator according to claim 9 , having 6N ring sectors.