Cooled IBR for a micro-turbine
AssigneeFlorida Turbine Technologies, Inc.
InventorsJack W Wilson, Jr., John E Ryznic, James P Downs
Life of this patent
Estimating the term…
Abstract
A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.
Claims11
A process for making an air cooled integral bladed rotor for a micro gas turbine engine, the process comprising the steps of:
- forming an IBR with a rotor disk and a plurality of turbine rotor blades extending from the rotor disk;
- machining a first radial extending cooling air channel from the blade tip and extending into the blade root;
- and,
- machining a first axial extending cooling air channel into the blade root from a forward side of the rotor disk to connect to the first radial extending cooling air channel.
A micro gas turbine engine comprising:
- a first stage turbine stator vane located downstream from a combustor;
- a first stage turbine rotor blade located downstream from the first stage turbine stator vane;
- the first stage turbine rotor blade being formed as an integral bladed rotor;
- the first stage turbine stator vane having an inner shroud with an annular air riding seal extending from an aft side of the inner shroud, the air riding seal forming a floating air seal with a forward side of the integral bladed rotor;
- the first stage turbine stator vane having a cooling air passage that supplies cooling air through the stator vane and to the annular air riding seal;
- the integral bladed rotor having an axial extending cooling air channel opening on the forward side and a radial extending cooling air channel connected to the axial extending cooling air channel;
- and,
- the axial extending cooling air channel being in fluid communication with the air riding seal to supply cooling air from the stator vane and into the radial extending cooling air channel to provide cooling for the turbine rotor blade.
Dependencies are inferred from the claim text.