Cooling arrangement for gas-turbine components

US6261053A · kind A · utility

Assignee

• Asea Brown Boveri, S.A. · CH

Inventors

• Gordon Anderson · Baden, CH
• Jorgen Ferber · Waldshut-Tiengen, DE
• Kenneth B. Hall · Gainesville, US
• Michael Hock · Münstermaifeld, DE
• Fathi Tarada · Kehrsatz, CH
• Bernhard Weigand · Lauchringen, DE

Key dates

• Filing date: Sep 14, 1998
• Grant date: Jul 17, 2001
• Expiry date: Sep 14, 2018

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A hot-gas stream (40) flows along the surface of a segment arrangement for shroud bands, in particular in a gas turbine. The segment arrangement comprises segments (20, 20') arranged next to one another and in each case separated from one another by a gap (12). The hot-gas stream (40), in at least one section (70) of the gap (12), has a velocity component perpendicular to the direction of the gap from a first segment (20) to a second segment (20'). In this case, in said section (70), along that edge (26) of the first segment (20) which faces the gap (12), at least one film-cooling bore (52) connects a cooling-air chamber (50), allocated to the first segment, to the surface (22) subjected to the hot-gas stream (40), and/or, in said section (70), along that edge (26') of the second segment (20') which faces the gap (12), at least one edge-cooling bore (56) connects a cooling-air chamber (50'), allocated to the second segment, to the inside (28') of the gap (12).