METHOD OF COOLING A GAS TURBINE AND APPARATUS
First Claim
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1. A method of designing a gas turbine engine comprising:
- locating purge openings in fluid communication with a first stage cavity;
positioning at least one of a cover plate or a rotor disk adjacent the first stage cavity and radially inward from the purge openings;
positioning a portion of a rotor blade radially outward from the purge openings; and
selecting a mass flow rate of cooling air through the purge openings based on a radial location of the purge openings to create an air barrier between a radially inner side of the purge openings and a radially outer side of the purge openings.
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Abstract
A method of designing a gas turbine engine includes locating purge openings in fluid communication with a first stage cavity. At least one of a cover plate or a rotor disk is positioned adjacent the first stage cavity and radially inward from the purge openings. A portion of a rotor blade is positioned radially outward from the purge openings. A mass flow rate of cooling air through the purge openings is selected based on a radial location of the purge openings to create an air barrier between a radially inner side of the purge openings and a radially outer side of the purge openings.
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Citations
20 Claims
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1. A method of designing a gas turbine engine comprising:
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locating purge openings in fluid communication with a first stage cavity; positioning at least one of a cover plate or a rotor disk adjacent the first stage cavity and radially inward from the purge openings; positioning a portion of a rotor blade radially outward from the purge openings; and selecting a mass flow rate of cooling air through the purge openings based on a radial location of the purge openings to create an air barrier between a radially inner side of the purge openings and a radially outer side of the purge openings. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine comprising:
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a first vane assembly; a first rotor assembly located axially aft of the first vane assembly; a cover plate engaging the first vane assembly and the first rotor assembly, wherein the first vane assembly, the first rotor assembly, and the cover plate at least partially define a first stage cavity, and a plurality of purge openings in fluid communication with the first stage cavity and located radially outward from the cover plate. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification