High compressor build clearance reduction
First Claim
1. A system comprising:
- a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%, wherein the cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine; and
at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.
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Accused Products
Abstract
An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.
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Citations
20 Claims
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1. A system comprising:
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a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%, wherein the cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine; and at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A method comprising:
executing a bowed rotor mitigation process on a gas turbine engine using at least one bowed rotor management system, the gas turbine engine comprising a high compressor having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%, wherein the cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine, wherein at least two bowed rotor management systems for the gas turbine engine are provided to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
Specification