IP Library › Granted Patent US 11,286,778
Granted Patent B2
US 11,286,778 · App. 17/276,680 · Granted Mar 29, 2022

Method for extracting a foreign body lodged in a high-pressure distributor blade

Inventors: Jean-Claude Milliasseau (Moissy-Cramayel, FR); Christophe Marie Pierre Michel Jehn (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
F01D5/005F01D5/288F01D5/147F01D5/187F01D9/065F05D2230/10F05D2230/237F05D2230/40F05D2230/80F05D2260/607
View Patent ↗
Loading inventors, assignments & file history…
Monitor This Case
Get email alerts when status or documents change.
Order Certified Copies
Most orders are placed with the USPTO same day — all within 24 business hours.
Order via The Patent Place →
Pre-filled with this patent's details
Quick Facts
Patent No.
US 11,286,778
App. No.
17/276,680
Granted
Mar 29, 2022
Kind
B2
Abstract

A method for extracting at least one foreign body lodged within a blade of a high-pressure distributor of a turbojet engine, the high-pressure distributor including hollow fixed blades between two annular shrouds forming a gas flow path, each blade being coated with a thermal barrier and provided with at least one recess at least partially obstructed by a first soldered closing plate, includes the following operations: cutting off the first closing plate, extracting the foreign body from the recess, carrying out an endoscopic inspection of an internal space of the recess in order to verify that no foreign body remains, positioning a second closing plate on the recess, and soldering the second closing plate directly onto the distributor with the blades coated with the thermal barrier.

Claims (12)

1. A method for extracting at least one foreign body lodged within a blade of a high-pressure distributor of a turbojet engine, said high-pressure distributor including fixed hollow blades between two annular shrouds forming a gas flow stream, each blade being coated with a thermal barrier and drilled with at least one cavity at least partially obstructed by a first brazed closing plate, the method comprising:

cutting the first brazed closing plate,

extracting the foreign body out of the cavity,

endoscopically inspecting an internal space of the cavity to check that no foreign bodies remain,

positioning a second closing plate on the cavity, and

brazing the second closing plate directly to the distributor with the blades coated with the thermal barrier.

2. The extraction method according to claim 1 , wherein cutting the first brazed closing plate is performed by grinding said plate.

3. The extraction method according to claim 1 , wherein positioning the second closing plate is performed by jig boring on the high-pressure distributor.

4. The extraction method according to claim 1 , wherein the second closing plate is pre-sintered.

5. The extraction method according to claim 1 , wherein brazing the second closing plate is performed in a vacuum furnace at a temperature below 1200° C.

6. The extraction method according to claim 5 , wherein brazing the second closing plate includes a thermal cycle performed at a temperature of between approximately 1160° C. and 1200° C. for 10 to 20 minutes, and then a diffusion cycle at a temperature of between approximately 1150° C. and 1200° C. for 2 to 4 hours.

7. The extraction method according to claim 1 , further comprising, after brazing the second closing plate, an operation of X-ray inspecting the high-pressure distributor.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Apr 19, 2021
From: MILLIASSEAU, JEAN-CLAUDE; JEHN, CHRISTOPHE MARIE PIERRE MICHEL
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 055961/0797 →
Priority Claims (1)
FR 1858353 · Sep 17, 2018 · national
Continuity (1)
Related Publication 20210293147A1 · Sep 23, 2021