Rotor blade tip clearance control
AssigneeROLLS-ROYCE plc
InventorsMarko BACIC, Leo Vivian LEWIS, Robert John IRVING
Life of this patent
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Abstract
A gas turbine engine comprising first and second axially spaced turbine rotor stages (46, 48) and a turbine casing (56) radially outside the rotor stages. A first seal segment arrangement (58) forms a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56). A first air source (82) is coupled to the first seal segment arrangement (58). A second seal segment arrangement (70) forms a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56). A heating chamber (84) is provided radially between the second seal segment arrangement (70) and the turbine casing (56). A duct (86) is coupled between the first air source (82) and the heating chamber (84).
Claims21
A gas turbine engine (10) comprising:
- a first turbine rotor stage (46) and a second turbine rotor stage (48), the first and second turbine rotor stages (46, 48) being axially spaced;
- a turbine casing (56) radially outside the first and second turbine rotor stages (46, 48);
- a first seal segment arrangement (58) forming a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56);
- a first air source (82) coupled to the first seal segment arrangement (58);
- a second seal segment arrangement (70) forming a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56);
- a heating chamber (84) radially between the second seal segment arrangement (70) and the turbine casing (56);
- and
- a duct (86) coupled between the first air source (82) and the heating chamber (84).
Dependencies are inferred from the claim text.