Inner blade support ring of a turbomachine compressor stator

Patent metadata

Field	Value
Publication number	US-12129763-B2
Application number	US-202218274645-A
Country	US
Kind code	B2
Filing date	Feb 2, 2022
Priority date	Feb 5, 2021
Publication date	Oct 29, 2024
Grant date	Oct 29, 2024

Abstract

An inner ring for supporting variable-pitch blades of an axial compressor stator of a turbomachine includes two or more ring sectors, assembled to form the inner ring, each ring sector including plural housings for receiving a pivot axis of one of the blades. At each junction plane between the ends of two successive ring sectors, an assembly pin and a cavity for receiving the assembly pin are engaged. The assembly pin is fixed on one end one of the two successive ring sectors and the cavity is formed at the end of the other of the two successive ring sectors. The cavity receives the assembly pin with a mounting clearance allowing a mounting by sliding fit, and the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the successive ring sectors.

First claim

The invention claimed is:

1. An inner ring comprising at least two ring sectors, assembled circumferentially end to end so as to form the inner ring, each of the at least two ring sectors comprising a plurality of housings for receiving a radially inner pivot axis of one of a plurality of variable-pitch blades,
wherein each of the at least two ring sectors has two ends,
wherein there is a junction plane between the two ends of the at least two ring sectors that form an assembly,
wherein at each junction plane between the two ends of the at least two ring sectors that that from the assembly of two successive ring sectors, the assembly of the two successive ring sectors is performed by cooperation of an assembly pin and a cavity for receiving the assembly pin, the assembly pin being fixed on one of the two ends of one of the two successive ring sectors and the cavity being formed at one of the two ends of the other of the two successive ring sectors,
wherein the cavity is configured and dimensioned to receive the assembly pin with a mounting clearance allowing a mounting by sliding fit,
and wherein the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the two successive ring sectors so that during a temperature rise, the assembly pin expands more inside the cavity than the cavity itself, thus ensuring the inseparable assembly of the two successive ring sectors and so that during a temperature decrease, the assembly pin retracts inside the cavity, by allowing a dismounting of the two successive ring sectors.

2. The inner ring according to claim 1 , wherein each of the at least two ring sectors has the cavity for receiving the assembly pin at a first end of the two ends of the ring sector and has the assembly pin at a second end of the two ends of the ring sector.

3. The inner ring according to claim 1 , wherein at least one of the at least two ring sectors has, at each of its two ends, the cavity for receiving the assembly pin and wherein at least one other of the at least two ring sectors has, at each of its two ends, the assembly pin.

4. The inner ring according to claim 1 , wherein the inner ring comprises two of the at least two ring sectors assembled end to end to form said inner ring.

5. The inner ring (according to claim 1 , wherein a ratio between the coefficient of thermal expansion of the material constituting the assembly pin and the coefficient of thermal expansion of the material constituting the at least two ring sectors is greater than or equal to 1.3 and less than 2.

6. The inner ring according to claim 1 , wherein a ratio between the coefficient of thermal expansion of the material constituting the assembly pin and the coefficient of thermal expansion of the material constituting the at least two ring sectors (is greater than or equal to 2.

7. The inner ring according to claim 1 , wherein the material constituting the assembly pin is chosen from aluminum or a nickel-based steel and wherein the material constituting the at least two ring sectors is chosen from steel or titanium.

8. The inner ring according to claim 1 , wherein the assembly pin is cylindrical wherein the cavity for receiving this assembly pin is cylindrical in shape.

9. An axial turbomachine compressor stator comprising:
the inner ring according to claim 1 ; and
the plurality of variable-pitch blades, pivotally mounted between an outer casing for supporting the variable-pitch blades and the inner ring for supporting the variable-pitch blades.

10. An axial turbomachine compressor, comprising at least one of the axial turbomachine compressor stator according to claim 9 .

11. A turbomachine comprising at least one of the axial turbomachine compressor according to claim 10 .

Assignees

• Safran Aircraft Engines

Inventors

• Cornec Nicolas Gérard Bénito

Classifications

• F05D2260/60

  Fluid transfer · CPC title

• F05D2240/128

  Nozzles · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F04D29/64

  of axial pumps · CPC title

• F04D29/563 Primary

  specially adapted for elastic fluid pumps · CPC title