High pressure ratio twin spool industrial gas turbine engine with dual flow high spool compressor
First Claim
1. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:
- a high pressure spool with a high pressure compressor and a high pressure turbine;
a electric generator connected to the high pressure spool to produce electrical power;
a low pressure spool with a low pressure compressor and a low pressure turbine;
the high pressure spool and the low pressure spool being capable of rotating independently;
an outlet of the low pressure compressor of the low pressure spool being connected to an inlet of the high pressure compressor of the high pressure spool;
the high pressure compressor having a first flow path to supply compressed air at a first pressure to a combustor;
the high pressure compressor having a second flow path concentric with the first flow path to supply compressed air at a second pressure higher than the first pressure to an air cooled airfoil within the high pressure turbine; and
,cooling air from the air cooled airfoil is discharged into the combustor.
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Accused Products
Abstract
An industrial gas turbine engine for electrical power production includes a high pressure spool and a low pressure spool in which the low pressure spool can be operated from full power mode to zero power mode when completely shut off, where the low pressure spool is operated at high electrical demand to supply compressed air to the high pressure compressor of the high pressure spool, and where turbine exhaust is used to drive a second electric generator from steam produced in a heat recovery steam generator. The high pressure spool includes a high pressure compressor with a inner compressed air flow path and an outer compressed air flow path in which a higher pressure supplies cooling to a turbine airfoil that is then discharged into a combustor of the engine.
20 Citations
11 Claims
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1. An industrial gas turbine engine for electrical power production, the industrial gas turbine engine comprising:
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a high pressure spool with a high pressure compressor and a high pressure turbine; a electric generator connected to the high pressure spool to produce electrical power; a low pressure spool with a low pressure compressor and a low pressure turbine; the high pressure spool and the low pressure spool being capable of rotating independently; an outlet of the low pressure compressor of the low pressure spool being connected to an inlet of the high pressure compressor of the high pressure spool; the high pressure compressor having a first flow path to supply compressed air at a first pressure to a combustor; the high pressure compressor having a second flow path concentric with the first flow path to supply compressed air at a second pressure higher than the first pressure to an air cooled airfoil within the high pressure turbine; and
,cooling air from the air cooled airfoil is discharged into the combustor. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A multiple stage compressor for an industrial gas turbine engine comprising:
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a rotor; a plurality of rows of rotor blades extending from the rotor; a plurality of rows of stator vanes extending from a stationary housing of the multiple stage compressor; the rows of rotor blades and rows of stator vanes each having a shroud to separate an inner compressed air flow path from an outer compressed air flow path; and
,the outer compressed air flow path makes up around 20% of the multiple stage compressor. - View Dependent Claims (9, 10)
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11. A multiple stage compressor for an industrial gas turbine engine comprising:
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a rotor; a plurality of rows of rotor blades extending from the rotor; a plurality of rows of stator vanes extending from a stationary housing of the multiple stage compressor; the rows of rotor blades and rows of stator vanes each having a shroud to separate an inner compressed air flow path from an outer compressed air flow path; the rows of rotor blades and rows of stator vanes each having a shroud to separate an inner compressed air flow path from an outer compressed air flow path; the inner compressed air flow path makes up around 20% of the multiple stage compressor; a second compressor downstream from a first compressor; the second compressor connected to the same rotor as the first compressor; the second compressor includes multiple rows of rotor blades and stator vanes; and
,the second compressor forms a continuation of the inner compressed air flow path of the first compressor to further compress the air from the inner flow path.
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Specification