Turbine distributor sector for an aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-10704419-B2
Application number	US-201816211134-A
Country	US
Kind code	B2
Filing date	Dec 5, 2018
Priority date	Dec 6, 2017
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

Abstract

Turbine distributor sector for an aircraft turbine engine, including an external annular platform sector and an internal annular platform sector, the sectors being coaxial and being connected together by blade assemblies including inner cavities cooled by gas circulation, the external platform sector including through openings of which radially internal ends open into the inner cavities, wherein the external platform sector includes inner ducts for supplying the cavities with gas, the ducts including air outlets opening into the openings and air inlets opening onto a portion of the external annular surface of the external platform sector.

First claim

The invention claimed is:

1. A turbine distributor sector for an aircraft turbine engine, comprising an external annular platform sector and an internal annular platform sector, said sectors being coaxial and being connected together by blade assemblies comprising inner cavities cooled by gas circulation, the external platform sector comprising through openings of which radially internal ends open into said inner cavities, wherein said external platform sector comprises inner ducts for supplying said cavities with gas, said ducts comprising air outlets opening into said openings and air inlets opening onto a portion of the external annular surface of the external platform sector.

2. The turbine distributor sector according to claim 1 , wherein each one of said openings extends at least partially into a boss protruding over a portion of the external annular surface of the external platform sector, each one of said ducts extending at least partially into this boss.

3. The turbine distributor sector according to claim 1 , wherein the air inlets are located on a portion of the external cylindrical surface of an annular rim, for attaching of the distributor to a turbine casing.

4. The turbine distributor sector according to claim 3 , wherein the annular rim has in its axial section locally a general L shape and comprises a substantially radial wall sector and a cylindrical wall sector that extends on the side of the openings from the radial wall sector.

5. The turbine distributor sector according to claim 4 , wherein each one of said openings extends at least partially into a boss protruding over a portion of the external annular surface of the external platform sector, each one of said ducts extending at least partially into this boss, and wherein the cylindrical wall sector is connected to each one of said bosses by material excess thicknesses into which said ducts extend at least partially.

6. The turbine distributor sector according to claim 1 , wherein each one of said air outlets opens into said opening, between a radially external end of this opening and an internal peripheral shoulder of the opening which is configured to support a ventilation jacket engaged in said inner cavity.

7. The turbine distributor sector according to claim 1 , wherein said air outlets each have a general elongated shape in a plane that is substantially parallel to the external platform sector.

8. The turbine distributor sector according to claim 1 , wherein the external platform sector comprises an upstream end with an axial section in the general shape of a C which defines an annular space oriented axially on the side opposite said openings, this end comprising an external annular rim and an internal annular rim which is serrated and comprises a series of axial teeth.

9. A turbine of an aircraft turbine engine, comprising a turbine casing extending around an axis of the turbine and carrying an annular row of distributor sectors according to claim 1 , wherein said portions of the external annular surface of the distributors bear against an annular wall of the casing, this annular wall of the casing comprising an annular row of orifices for supplying with air which are aligned with the air inlets present on the portions of the external annular surface of the distributors.

10. The turbine according to claim 9 , wherein each one of said openings extends at least partially into a boss protruding over a portion of the external annular surface of the external platform sector, each one of said ducts extending at least partially into this boss, wherein the cylindrical wall sector is connected to each one of said bosses by material excess thicknesses into which said ducts extend at least partially, and wherein the casing comprises an annular lug surrounded by the annular row of orifices and comprising axial teeth engaged circumferentially between said material excess thicknesses.

Assignees

• Safran Aircraft Engines

Inventors

• Bassery Josserand Jacques Andre
• Coetard Jean-Charles Marcel Bernard
• Dupeyre Raphael Jean Philippe
• Francois Etienne Leon
• Tang Ba-Phuc

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F05D2240/125

  related to the tip of a stator vane · CPC title

• F05D2240/81

  Cooled platforms · CPC title

• F05D2250/14

  elliptical · CPC title