Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

General Electric Technology Gmbh

Sergey Shchukin

Joerg Krueckels

Carlos Simon-Delgado

Robert Marmilic

Sergei Riazantsev

Stefan Rofka

Martin Schnieder

Daniel Seng

Sven Olmes

Thomas Kramer

Ernst Pauli

Holger Kiewel

Vasileios Stefanis

Hanspeter Knopfel

Thomas F Kramer

Hanspeter Knöpfel

A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.

Gas turbine cooling systems and methods

A turbine vane for a rotary turbomachine has a turbine blade delimited by a concave pressure-side wall and a convex suction-side wall which are connected in the region of a vane front edge which can be assigned to the turbine blade and enclose a cavity which extends in the longitudinal extent of the vane front edge and is delimited on the inner wall by the pressure-side wall and the suction-side wall in the region of the vane front edge and by an intermediate wall which extends in the longitudinal direction to the vane front edge and connects the suction-side wall and the pressure-side wall on the inner wall. The intermediate wall has a perforation at least in sections in the connecting region to the suction-side wall and/or pressure-side wall, in order to increase the elasticity of the intermediate wall.

Turbine blade

The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.

Cooled wall

A high-pressure compressor (), in particular in a gas turbine (), has a compressor rotor () which is surrounded by a stator () thereby forming a main flow channel () and which is delimited at the compressor outlet by an end face () substantially extending in the radial direction, along which end face cooling air () is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face () is provided with a first system () for improving the heat transfer between the cooling air () and the end face ().

High pressure compressor

A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.

Gas turbine engine and method for cooling the compressor of a gas turbine engine

Growing community of inventors

Mellingen, Switzerland

Sergey Shchukin