IP Library Granted Patent US 9,657,579
Granted Patent B2
US 9,657,579 · App. 14/427,295 · Granted May 23, 2017

Cooled vane of a high-pressure turbine

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Quick Facts
Patent No.
US 9,657,579
App. No.
14/427,295
Granted
May 23, 2017
Kind
B2
Abstract

The invention relates to a movable vane of a turbomachine comprising a blade ( 12 ) with inner cooling cavities and a root ( 11 ) by which means the vane can be mounted on a rotor disk, the root comprising at least two channels ( 11 a ) communicating with said inner cavities and leading to the base ( 11 b ) thereof, said base comprising at least two openings ( 11 b 1, 11 b 2 ) through which the channels open up, and a calibrating plate ( 20 ) provided with calibrated perforations ( 21, 22 ) corresponding to said openings being attached to the base ( 11 b ) of the root. The vane is characterized in that a mechanical means ( 25, 26; 11 m 1, 11 m 2 ) forming a sealing barrier between the two openings is arranged between the plate and the base of the root.

Claims (8)

1. Movable vane of a turbine engine comprising a blade having inner cooling cavities and a root by means of which the vane can be mounted on a rotor disc, the root comprising at least two channels communicating with said inner cavities and opening out on the base, said base comprising at least two openings through which the channels open out, and a calibrating plate provided with calibrated perforations corresponding to said openings being attached to the base of the root, characterised in that a mechanical means forming a sealing barrier between the two openings is arranged between the plate and the base of the root, said means comprising a tenon arranged on the plate or base of the root and a mortise arranged facing the tenon on the base or plate, the tenon being slotted into the mortise.

2. Vane according to claim 1 , wherein at least one face of the tenon is in contact with the wall of the mortise in such a way as to prevent any passage of gas between the tenon and the mortise.

3. Vane according to claim 1 , wherein the tenon has a trapezoidal cross section.

4. Vane according to claim 1 , wherein the tenon has a rounded cross section.

5. Vane according to claim 1 , wherein the plate is attached to the vane root by autogenous welding.

6. Vane according to claim 5 , wherein the weld is a lap weld around the perimeter of the plate.

7. Vane according to claim 1 wherein the plate is attached by brazing.

8. Vane according to claim 1 , comprising between two and six openings on the base, mechanical sealing means being arranged in the separation regions between the openings.

Assignments (3)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Mar 10, 2015
From: BOTREL, ERWAN DANIEL; DUJOL, CHARLOTTE, MARIE
To: SNECMA
Reel/Frame 035131/0946 →