Operation of a Gas Turbine at High Temperature and Gas Turbine Arrangement

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This patent describes a method for operating gas turbines at extremely high temperatures (above 1000°C, and even above 1500°C) by utilizing structural materials protected by a thermal insulation layer, such as yttria-stabilized zirconia (YSZ). The key innovation is a controlled, slowed-down cooling process after high-temperature operation, which minimizes damage to both the turbine's structural material and insulation layer. The turbine is also designed with a specific cooling rate and can include a control system to manage performance reduction and cooling, enabling safe, long-term high-temperature operation and improving turbine efficiency.

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• Power plants with stationary gas turbines to improve efficiency and lifespan during long-term high-temperature operation.
• Aerospace applications where aircraft turbines operate at high temperatures and require slow cooling to prevent material damage.
• Industrial gas turbines used for process heat or electricity generation in refineries, chemical plants, or manufacturing facilities.
• Retrofit or upgrade solutions for existing gas turbines, enabling higher operational temperatures while reducing wear and tear.

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• Enables safe, sustained operation of gas turbines at very high temperatures (above 1500°C), increasing efficiency and power output.
• Reduces thermal stress and damage in turbine materials and insulation, extending the lifespan of critical components.
• Minimizes expensive maintenance and replacement costs typically associated with high-temperature operations.
• Allows for simpler insulation layer designs (potentially single-layered), leading to reduced manufacturing complexity and cost.
• Improves the stability and durability of turbine thermal barrier coatings, supporting long-term reliable power generation.
• Provides a method for precise temperature control during both heating and cooling, reducing the risk of sudden material failures.

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Patent Abstract

The invention relates to a method for operating a gas turbine at a high temperature and a gas turbine assembly. In the method, after operation with an operating temperature above 1000°C, a gas turbine (1) having a structural material (2) and a thermal insulation layer (3) arranged on the structural material (2) is cooled in a slowed manner, such that damage to the structural material (2) and/or the thermal insulation layer (3) is minimised. In this way, the gas turbines can be operated at temperatures above 1500°C in the long term.