Turbine last stage rotor blade with forced driven cooling air

Patent metadata

Field	Value
Publication number	US-9810151-B2
Application number	US-201414512070-A
Country	US
Kind code	B2
Filing date	Oct 10, 2014
Priority date	Aug 24, 2013
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

A turbine of a gas turbine engine with a rotor and a stator forming a rim cavity, where the rotor includes a turbine rotor blade with a cooling air channel opening into the rim cavity, and a centrifugal impeller rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel.

First claim

I claim the following:

1. A gas turbine engine comprising:
a turbine with a rotor and a stator;
a turbine rotor blade extending from the rotor;
a centrifugal impeller rotatably connected to the rotor;
a rim cavity formed between the rotor and the stator;
a seal formed between the rotor and the stator to form a seal between the rim cavity and a hot gas path through the turbine;
a cooling air channel formed in the rotor and the turbine rotor blade with an opening into the rim cavity;
the centrifugal impeller located on the rotor such that rotation of the rotor and centrifugal impeller discharges pressurized cooling air into the rim cavity and then through the cooling air channel formed in the rotor and turbine rotor blade; and,
the centrifugal impeller having an axial inlet and a radial outlet.

2. A gas turbine engine comprising:
a turbine with a rotor and a stator;
a turbine rotor blade extending from the rotor;
a centrifugal impeller rotatably connected to the rotor;
a rim cavity formed between the rotor and the stator;
a labyrinth seal formed between the rotor and the stator to form a seal between the rim cavity and a hot gas path through the turbine;
a cooling air channel formed in the rotor and the turbine rotor blade with an opening into the rim cavity; and,
the centrifugal impeller located on the rotor such that rotation of the rotor and centrifugal impeller discharges pressurized cooling air into the rim cavity and then through the cooling air channel formed in the rotor and turbine rotor blade.

3. A gas turbine engine comprising:
a turbine with a rotor and a stator;
a turbine rotor blade extending from the rotor;
a centrifugal impeller rotatably connected to the rotor;
a rim cavity formed between the rotor and the stator;
a seal formed between the rotor and the stator to form a seal between the rim cavity and a hot gas path through the turbine;
a cooling air channel formed in the rotor and the turbine rotor blade with an opening into the rim cavity;
the centrifugal impeller located on the rotor such that rotation of the rotor and centrifugal impeller discharges pressurized cooling air into the rim cavity and then through the cooling air channel formed in the rotor and turbine rotor blade; and,
a shroud secured to the stationary casing and enclosing blades of the centrifugal impeller.

Assignees

• Brostmeyer Joseph D
• Florida Turbine Tech Inc

Inventors

• Brostmeyer Joseph D

Classifications

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2220/3215

  the last stage of the turbine · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title