Cooled turbine-nozzle vane

• US 6,109,867 A
• Filed: 11/25/1998
• Issued: 08/29/2000
• Est. Priority Date: 11/27/1997
• Status: Expired due to Term

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Jacques Portefaix, Laurent Roger
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/199,777
• Time in Patent Office: 643 Days
• Field of Search: 415/115, 415/174.5, 415/110, 415/116, 415/173.4, 415/173.5, 415/173.7, 415/174.4, 416/96 A, 416/96 R, 416/97 R
• US Class Current: 415/115
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine-nozzle vane fitted with a cooling system including a hollow airfoil (45) inserted between an outer deck and an inner deck (46). Disposed inside the airfoil (45) is a liner (60) which is fitted with a multi-perforated skirt to impact-cool the airfoil wall. The liner (60) has an inner wall (62) comprising a female frustum of a cone (66). A male frustum of a cone (64) is rigidly affixed to the inner deck (46) and is nested in the female frustum (66). These frusta provide communication between the inside of the liner (60) and the inside of the inner deck (46). Cooling air (70) is introduced into the liner (60) through the outer deck. A portion (71) of this air impact-cools the airfoil wall. Another portion (72) enters the inner deck (46) and passes through an orifice (67) to cool the turbine disks (49, 50) upstream and downstream of the nozzle.

Claims

1. A turbine-nozzle vane fitted with a cooling system, said vane comprising:

a hollow airfoil (45) inserted between a hollow outer deck (76) and a hollow inner deck (46), the inner deck (46) having an outer wall (63) with an intake orifice formed therein and an upstream wall with an exhaust orifice (67) formed therein;

a liner (60) mounted inside the airfoil (45) to define a cavity therebetween and bounded thereby, the liner (60) being fitted with a multi-perforated skirt (61) and an inner wall (62), the skirt being kept spaced apart from the airfoil (45);

an outlet orifice formed in the inner wall (62) of the liner (60) opposite the intake orifice in the outer wall (63) of the inner deck (46); and

a seal providing communication between the outlet orifice in the inner wall (62) of the liner (60) and the intake orifice in the outer wall (63) of the inner deck (46), the seal precluding direct communication between the inner deck (46) and the cavity bounded by the airfoil (45) and the liner (60);

wherein a cooling airflow (70) is fed into the liner (60) from the outer deck (76) with a portion (71) impact-cooling the airfoil (45) through the multi-perforated skirt (61) and the other portion (72) circulating in the inner deck (46) through the seal and then exhausting through the exhaust orifice (67) to cool turbine disks (49,50) of a gas-turbine engine; and

wherein the seal comprises a hollow female frustum of a cone (66) having a top aperture, the female frustum (66) being rigidly joined to the inner wall (62) of the liner (60) and bounding the outlet orifice, a hollow male frustum of a cone (64) having a top aperture, the male frustum (64) being rigidly joined to the outer wall (63) of the inner deck (46) and bounding the intake orifice, and wherein the male frustum (64) is nested in the female frustum (66) with the top apertures disposed within the liner (60).