Cooling of components
AssigneeROLLS-ROYCE plc
InventorsHaidong Li, Caner H Helvaci
Life of this patent
Estimating the term…
Abstract
A geared gas turbine engine is shown. It comprises a high pressure turbine configured to drive a compressor and a low pressure turbine configured to drive a propulsor via a reduction gearbox. The high pressure turbine comprises a turbine stage, and the turbine stage comprises a set of nozzle guide vanes, NGVs, and a plurality of turbine blades downstream of the set of NGVs. A ratio, ε1, of a cooling mass flow for cooling the plurality of turbine blades of the turbine stage and a throat mass flow of the set of NGVs of turbine stage is between 0.040 and 0.075 at cruise conditions.
Claims20
A geared gas turbine engine comprising a high pressure turbine configured to drive a compressor and a low pressure turbine configured to drive a propulsor via a reduction gearbox, wherein:
- the high pressure turbine comprises a turbine stage, the turbine stage comprising a set of nozzle guide vanes, NGVs, and a plurality of turbine blades downstream of the set of NGVs;
- and
- a ratio, ε1, of a cooling mass flow for cooling the plurality of turbine blades of the turbine stage and a throat mass flow of the set of NGVs of turbine stage is between 0.040 and 0.075 at cruise conditions.
A method of operating a geared gas turbine engine comprising a high pressure turbine configured to drive a compressor and a low pressure turbine configured to drive a propulsor via a reduction gearbox, wherein:
- the high pressure turbine comprises a first turbine stage, the first turbine stage comprising a first turbine nozzle guide vane, NGV, and a first turbine blade downstream of the first turbine NGV;
- and
- the method comprises operating the geared gas turbine engine at cruise conditions, wherein a ratio, ε1, of a cooling mass flow for cooling the first turbine blade and a throat mass flow of the first turbine NGV is between 0.040 and 0.075 at the cruise conditions.
A geared gas turbine engine comprising a high pressure turbine configured to drive a compressor and a low pressure turbine configured to drive a propulsor via a reduction gearbox, wherein:
- the high pressure turbine comprises a first turbine stage, the first turbine stage comprising a first turbine nozzle guide vane, NGV, and a first turbine blade downstream of the first turbine NGV;
- and
- a ratio, ν1, of a cooling mass flow for cooling the first turbine NGV and a throat mass flow of the first turbine NGV is between 0.080 and 0.150 at cruise conditions.
Dependencies are inferred from the claim text.