A gas turbine installation (1), in particular in a power plant for generating electricity, includes a turboset (2) having a turbine (4), a compressor (5) and a combustion chamber (6) arranged in a gas path (9) connecting the compressor (5) to the turbine (4), and a flue gas recirculation device (3), which passes combustion flue gas from the turbine (4) from a flue gas path (14) connected to the turbine (4) via a recirculation path (16) to a fresh gas path (13) connected to the compressor (5). To improve the efficiency of the gas turbine installation (1), a control device (17) controls a volumetric flow and/or a temperature of the recirculated combustion flue gases in such a way that a fresh gas/flue gas mixture which enters the compressor (5) is at a predetermined desired temperature.

Gas turbine installation

A system includes a turbine casing including a first hook configured to mate with a second hook to support a turbine shroud about a plurality of turbine blades. The turbine casing includes a coolant circuit configured to adjust clearance between the turbine shroud and the turbine blades based on coolant flow through the coolant circuit. The coolant circuit includes a first plurality of radial coolant passages extending into the first hook.

System and method for clearance control in a rotary machine

A gas turbine engine includes an active clearance control (ACC) system within the engine casing (52). The case (52) includes a wall structure with a cast-in cooling configuration (68) through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth.

Gas turbine engine case for clearance control

A gas turbine that supplies combustion gas generated by supplying fuel to a combustor where the fuel is combusted with compressed air compressed at a compressor to a turbine to acquire rotational power, the gas turbine comprising pressurizing means connected to a branching channel branching from a discharge-side channel of the compressor and capable of carrying out an operation for introducing and pressurizing a temperature-control medium independently from the compressor, a temperature-control-medium supply channel that guides pressurized temperature-control medium pressurized at the pressuring means to a turbine-cooling-medium channel provided in a stationary component of the turbine, and a temperature-control-medium return channel that guide the pressurized temperature-control medium that has passed through the turbine-cooling-medium channel to the discharge-side channel such that the flows are combined, wherein the pressurizing means is operated at shutdown of the gas turbine to let the pressurized temperature-control medium flow in the turbine-cooling-medium channel.

Gas turbine and operating method thereof

An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance.

Active tip clearance control arrangement for gas turbine engine

Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

Hubert Edward Paprotna

Papers

System for actively controlling compressor clearances