Mixed Stator for an Axial Turbine Engine Compressor

Patent metadata

Field	Value
Publication number	US-2016130960-A1
Application number	US-201514926248-A
Country	US
Kind code	A1
Filing date	Oct 29, 2015
Priority date	Nov 6, 2014
Publication date	May 12, 2016
Grant date	—

Abstract

The present application relates to a stator for a low-pressure compressor of an axial turbine engine. The stator includes an annular row of stator vanes with connection vanes, and support vanes which are grouped into vaned casings. The casings include internal platforms and external platforms, and are integrally produced by means of additive production based on titanium powder. The stator has a circular internal shroud which is formed by the internal platforms of the vanes of the casings and internal shroud segments which are fixed to the connection vanes. The internal platforms include pairs of contact surfaces in order to interlock the shroud segments therein by moving into abutment and sliding against the contact surfaces. The contact surfaces are perpendicular to the rotation axis and form axial stops.

First claim

I claim:

1 . A stator assembly for an axial turbine engine, comprising:
an annular row of stator vanes comprising:
integral support vanes with internal platforms and connection vanes;
internal shroud segments;
an internal shroud formed by the internal platforms of the support vanes; and
internal shroud segments which are fixed to the connection vanes;
wherein an internal platform of a support vane comprises:
at least one contact surface which is generally perpendicular to the rotation axis of the turbine engine and which is axially in contact with an internal segment.

2 . The stator assembly in accordance with claim 1 , further comprising:
at least one integral vane block comprising:
a plurality of support vanes;
an internal platform which is common to each of the support vanes thereof; and
an external platform which is common to each of the support vanes thereof.

3 . The stator assembly in accordance with claim 2 , further comprising:
at least one casing comprising:
a plurality of support vanes which describe an angular portion of the annular row of vanes.

4 . The stator assembly in accordance with claim 1 , wherein at least one or each internal platform of a support vane comprises:
at least four contact surfaces which are generally perpendicular to the rotation axis of the turbine engine and which are in contact with two separate internal segments.

5 . The stator assembly in accordance with claim 1 , further comprising:
a plurality of contact surfaces which are formed on the internal platforms, the contact surfaces generally being parallel with each other and describing at least two circular rows.

6 . The stator assembly in accordance with claim 1 , wherein at least one platform comprises:
a pair of contact surfaces which are in contact with the same segment and which are orientated axially in opposing directions.

7 . The stator assembly in accordance with claim 1 , wherein each internal segment is adjusted mechanically to each internal platform with which it is in contact in order to enable retention by means of interlocking.

8 . The stator assembly in accordance with claim 1 , wherein the internal segments are interposed between the internal platforms of support vanes, the segments and the platforms form an alternating arrangement which is generally regular.

9 . The stator assembly in accordance with claim 1 , wherein each contact surface of the internal platform is configured to enable a radial introduction of an internal segment from the inner side.

10 . The stator assembly in accordance with claim 1 , wherein at least one internal platform is profiled and comprises:
a profile which has an axial portion which extends principally axially and two radial portions which extend principally radially towards the inner side from the axial portion, each radial portion being arranged at one of the upstream and downstream ends of the axial portion, each contact surface being formed on one of the radial portions.

11 . The stator assembly in accordance with claim 1 , wherein at least one or each support vane is integral and produced by additive manufacturing based on powder.

12 . The stator assembly in accordance with claim 1 , wherein at least one internal segment is produced from a composite material including fibers and an organic matrix.

13 . The stator assembly in accordance with claim 1 , wherein at least one segment comprises:
a plurality of corresponding contact surfaces which are adapted to move into contact with each contact surface of an associated platform during their assembly.

14 . The stator assembly in accordance with claim 1 , wherein at least one internal platform comprises:
an internal groove which is radially open towards the inner side, the segment comprising:
a portion of smaller radial and axial thickness which is introduced into the internal groove of the associated support vane.

15 . A compressor of an axial turbine engine, the compressor including a bladed rotor and a stator, the stator comprising:
an annular row of stator vanes comprising:
integral support vanes with internal platforms and connection vanes;
an internal shroud formed by the internal platforms of the support vanes; and
internal shroud segments which are fixed to the connection vanes, the internal shroud encircling the rotor;
wherein an internal platform of a support vane comprises:
at least one contact surface which is generally perpendicular to the rotation axis of the turbine engine and which is axially in contact with an internal segment.

16 . The compressor in accordance with claim 15 , further comprising:
an outer housing which is formed by two half-shells, each provided with a semi-circular wall and axial fixing flanges in order to join the half-shells, an internal platform of a support vane being aligned with each axial flange along the circumference.

17 . The compressor in accordance with claim 16 , wherein two internal platforms of two support vanes are arranged at one side and the other of an interface between axial flanges which are fixed together.

18 . The compressor in accordance with claim 16 , wherein each internal platform has two opposing edges along the circumference of the row of vanes, the support vane corresponding to each platform has at least one fixing shaft which is arranged remote from the edges and remote from each axial flange of a half-shell.

19 . The compressor in accordance with claim 15 , wherein the internal shroud comprises:
an annular abradadable layer, the contact surface being in contact with the annular abradadable layer.

20 . A turbine engine comprising:
a rotor; and a stator comprising:
an annular row of stator vanes having integral support vanes with internal platforms and connection vanes; and
an internal shroud formed by the internal platforms of the support vanes and internal shroud segments which are fixed to the connection vanes, the internal shroud encircling the rotor;
wherein an internal platform of a support vane comprises:
at least one contact surface which is axially in contact with an internal segment, the rotor radially faces the contact surface.

Assignees

• Techspace Aero Sa

Inventors

• Cortequisse Jean-François

Classifications

• F01D9/06

  Fluid supply conduits to nozzles or the like · CPC title

• F05D2300/40

  Organic materials · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title