Gas turbine engine
AssigneeROLLS-ROYCE plc
InventorStephen J. Bradbrook
Life of this patent
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Abstract
A gas turbine engine comprising: a combustor configured to initiate combustion; and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes; wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring. A method of starting a gas turbine engine is also described.
Claims18
A gas turbine engine comprising:
- a combustor configured to initiate combustion;
- and
- a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;
- wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring;
- and
- wherein the restrictor is an insert configured to cooperate with the stator vane to prevent downstream ejection of the restrictor prior to ablation.
A method of starting a gas turbine engine, the method comprising the steps of:
- providing a gas turbine engine comprising a combustor configured to initiate combustion and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;
- providing at least one of the passageways with a restrictor defining a temporary gas washed surface for the stator vane ring;
- and
- initiating combustion in the combustor to increase the temperature of flow exiting the combustor, thereby ablating the restrictor to reveal an operational gas washed surface of the stator vane ring;
- and
- wherein the restrictor is an insert, and wherein providing at least one of the passageways with the restrictor comprises installing the insert in the stator vane ring to cover an operational pas washed surface of the stator vane ring.
A gas turbine engine comprising:
- a combustor configured to initiate combustion;
- and
- a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;
- wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring;
- and
- wherein the restrictor is a coating formed from tin or an alloy of lead and tin.
Dependencies are inferred from the claim text.