Gas turbine engine
OwnerKyle JIANGinventor
Life of this patent
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Abstract
A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between the compressor and the turbine are spaced circumferentially about the shaft axis. The combustion chambers (10) are elongate in the direction of air/gas flow and the longitudinal axis of each combustion chamber is skewed transversely relative to the axis Z of the turbine shaft. The combustion chambers (10) may be curved longitudinally about the shaft axis and may be aligned concentric about the axis. The engine may have a recuperator (8) radially outboard the compressor, the recuperator having radially directed flow passages through which air from the compressor is directed.
Claims19
A gas turbine engine comprising a turbine shaft rotatable about an axis, a centrifugal compressor and a radial turbine each mounted to the shaft for rotation therewith about the axis, and a plurality of combustion chambers in an air/gas flow path between the compressor and the turbine;
- in which the combustion chambers are spaced circumferentially about the axis of the turbine shaft, each combustion chamber being elongate in the direction of air/gas flow through the combustion chamber, wherein the longitudinal axis of each combustion chamber is skewed generally in a transverse direction relative to the axis of the turbine shaft.
A gas turbine engine comprising a turbine shaft rotatable about an axis, a centrifugal compressor and a radial turbine each mounted to the shaft for rotation with the shaft about the axis, an annular recuperator circumferentially surrounding the centrifugal compressor, and at least one combustion chamber in an air/gas flow path between the recuperator and the turbine;
- in which the recuperator has a first set of flow passages for receiving compressed air from the centrifugal compressor, the first set flow passages extending in a radial direction, the recuperator having a second set of flow passages interleaved between the first flow passages, the second set of flow passages being fluidly connected with the turbine for receiving exhaust gas from the turbine.
Dependencies are inferred from the claim text.