Attaching the blades to the drum of an axial turbocompressor

Patent metadata

Field	Value
Publication number	US-9598968-B2
Application number	US-201314017961-A
Country	US
Kind code	B2
Filing date	Sep 4, 2013
Priority date	Sep 11, 2012
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it.

First claim

What is claimed is:

1. A bladed rotor of an axial turbomachine, said bladed rotor comprising:
a wall forming a circular web, at least one annular portion of the wall being raised relative to the web immediately at least one of upstream and downstream of the at least one annular portion of the wall, the at least one annular portion of the wall being provided with a row of blade mounting apertures;
a plurality of rotor blades, each rotor blade comprising:
a platform; and
two aerodynamic surfaces opposite each other and extending from the platform along a main axis of the blade;
the platform comprising, along the main axis of the blade,
a first portion forming a surface bounding a fluid stream and skirting the aerodynamic surfaces, and
a second portion located below the first portion relative to the aerodynamic surfaces and designed for attaching the blade; wherein
the second portion of the platform mates with an inner face of the annular portion of the wall of the rotor around one of the mounting apertures; and
the second portion forms one or more shoulders projecting from the surface of the first portion; and

an element, in each of the least one annular portion of the wall, for exerting pressure on the inner face of the platforms of the rotor blades to hold them in place.

2. The bladed rotor in accordance with claim 1 , wherein the second portion of the platform is designed to be able to
mate directly with portions of the inner surface of the wall of the rotor located circumferentially on both sides of the aperture.

3. The bladed rotor in accordance with claim 1 , wherein the second portion extends at least substantially parallel to the first portion and protrudes from the surface of the first portion to form a shoulder on each of its edges.

4. The bladed rotor in accordance with claim 1 , wherein, the wall portion is integral.

5. The bladed rotor in accordance with claim 1 , wherein the web comprises at least one annular rib designed to mate sealingly with an inner surface of an inner shell of a stator blade stage.

6. The bladed rotor in accordance with claim 1 , wherein the wall comprises at least one connecting portion extending mainly radially between the wall forming the web and the annular portion of the wall.

7. The bladed rotor in accordance with claim 1 , wherein the shape of the mounting apertures in the annular portion of the wall corresponds to that of the first portion of the platform of the blades and the boundary surfaces of the fluid stream of the first portion are flush with the outer surface of the annular portion of the wall.

8. The bladed rotor in accordance with claim 1 , wherein the second portion extends at least substantially parallel to the first portion and protrudes from the surface of the portion to form a shoulder on each of its edges, the shape of the mounting apertures in the annular portion of the wall corresponds to that of the first portion of the platform of the blades and the boundary surfaces of the fluid stream of the first portion are flush with the outer surface of the annular portion of the wall.

9. The bladed rotor in accordance with claim 1 , wherein the or each of the elements for exerting pressure comprises at least one of:
at least one snap ring, and
at least one strip arranged annularly.

10. The bladed rotor in accordance with claim 1 , further comprising a bonding material between the shoulders of the platforms of the blades and the wall of the rotor.

11. The bladed rotor in accordance with claim 10 , wherein the bonding material comprises glue.

12. The bladed rotor in accordance with claim 1 , wherein the mounting apertures in the annular portion of the wall and the blades are designed so as to allow the insertion of the blades through the apertures from inside the rotor for the purpose of fixing them.

13. A bladed rotor of an axial turbomachine, said bladed rotor comprising:
a wall forming a circular web, an annular portion of the wall being raised relative to the web immediately at least one of upstream and downstream of the annular portion of the wall, the annular portion of the wall being provided with a row of blade mounting apertures;
a plurality of rotor blades, each rotor blade comprising:
a platform; and
two aerodynamic surfaces opposite each other and extending from the platform along a main axis of the blade;
the platform comprising, along the main axis of the blade,
a first portion forming a surface bounding a fluid stream and skirting the aerodynamic surfaces, and
a second portion located below the first portion relative to the aerodynamic surfaces and designed for attaching the blade; wherein
the second portion protrudes from a lower face of the first portion and comprises an aperture oriented circumferentially relative to the rotor capable of mechanically engaging with a snap ring designed to come into contact with an inner surface of the wall, and wherein
a lower surface of the first portion bypasses the second portion and forms a support surface on the platform on a corresponding surface of the wall of the rotor.

14. The bladed rotor in accordance with claim 13 , wherein the outer surface of the annular portion of the wall comprises a cavity around each mounting aperture designed to house the first portion of the platform of the blades, the second portion of the platform of the blades extending through the aperture, and the snap ring mates with the apertures of the platforms of the blades and the inner surface of the portion of the wall, the snap ring being arranged annularly.

Assignees

• Techspace Aero Sa
• Safran Aero Boosters Sa

Inventors

• Englebert Eric

Classifications

• F01D5/3053

  by means of pins · CPC title

• F04D29/322

  Blade mountings · CPC title

• F01D5/3007 Primary

  of axial insertion type · CPC title

• F01D5/3023 Primary

  of radial insertion type, e.g. in individual recesses · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic