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A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at

A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid.

대표청구항 ▼

1. A gas turbine engine system configured for power generation, the gas turbine engine system comprising: a compressor, a combustor and a turbine, the compressor providing compressed air to the combustor for combustion with a fuel to produce a hot working gas and the turbine receiving the hot workin

1. A gas turbine engine system configured for power generation, the gas turbine engine system comprising: a compressor, a combustor and a turbine, the compressor providing compressed air to the combustor for combustion with a fuel to produce a hot working gas and the turbine receiving the hot working gas to produce power;the compressor and turbine of the gas turbine engine system being configured with reference to a reference engine, the reference engine defining a configuration having a predetermined compressor upper mass flow of air for a predetermined turbine inlet temperature to produce an optimum engine efficiency at a predetermined compressor inlet condition at a maximum power output for the reference engine, wherein the predetermined compressor inlet condition comprises ISO conditions for a gas turbine engine;the turbine comprising a configuration substantially identical to a turbine of the reference engine;the compressor having a configuration different than a compressor of the reference engine, wherein the compressor is sized larger than the compressor of the reference engine to provide a maximum flow capability of the compressor greater than an upper flow capability of the compressor of the reference engine;wherein the compressor comprises inlet guide vanes (IGVs) at an inlet to the compressor, the IGVs having a predetermined position for operating the gas turbine engine system at an optimum efficiency at the predetermined turbine inlet temperature, wherein the predetermined position of the IGVs reduces the mass flow of air into the compressor to a flow less than the maximum flow capability; andwherein the compressor comprises a plurality of stages, each stage defined by a row of stationary vanes and a row of rotating blades, and wherein about a front one-third of the stages of the compressor, at an inlet end thereof, are sized with a larger outer diameter than the corresponding stages of the compressor of the reference engine. 2. The gas turbine engine system of claim 1, wherein the predetermined position of the IGVs defines a mass flow of air entering the compressor for producing a base load output, and opening the IGVs from the predetermined position toward a more open position increases the power output of the gas turbine engine system. 3. The gas turbine engine system of claim 2, wherein the movement of the IGVs toward the more open position produces the increase in power output at a constant turbine inlet temperature defined by the predetermined turbine inlet temperature. 4. The gas turbine engine system of claim 3, wherein the increase in power output is an increase of at least 10% above the base load output with the movement of the IGVs toward the more open position. 5. The gas turbine engine system of claim 4, wherein the IGVs are movable from the predetermined position toward a closed position, reducing the mass flow of air to the compressor, wherein the IGVs are adapted to reduce the mass flow of air into the compressor at least 20% below the mass flow of air at the base load power output to provide a reduced part load power output. 6. The gas turbine engine system of claim 2, wherein the movement of the IGVs toward the more open position is adapted to provide a constant base load power output with increasing compressor inlet air temperatures above the predetermined compressor inlet condition.