Control of low pressure recoup air in a gas turbine engine disposed in a gas turbine enclosure with low pressure recoup air piping coupled to a gas turbine combustion exhaust and gas turbine engine enclosure is disclosed. A first valve of the piping controls a flow of the recoup air to the gas turbine combustion exhaust. A second valve of the piping diverts the recoup air to the enclosure for eventual flow to the air intake. A controller controls the flow of the recoup air from the piping to the exhaust and/or the enclosure as a function of ambient and air intake temperature measurements, and a predetermined temperature requirement having an ambient temperature constraint and an air intake temperature differential constraint.

A fracturing device, including a power unit, wherein the power unit comprises a muffling compartment, a turbine engine, an air intake unit, and a starter; the air intake unit is communicated with the turbine engine through an intake pipe, and configured to provide a combustion-supporting gas to the turbine engine; the air intake unit is located at the top of the muffling compartment, the muffling compartment comprises an accommodation space, the turbine engine and the starter are located in the accommodation space, and the starter is configured to start the turbine engine, the starter comprises a first electric motor.

A fracturing device, including a power unit, wherein the power unit comprises a muffling compartment, a turbine engine, an air intake unit, and a starter; the air intake unit is communicated with the turbine engine through an intake pipe, and configured to provide a combustion-supporting gas to the turbine engine; the air intake unit is located at the top of the muffling compartment, the muffling compartment comprises an accommodation space, the turbine engine and the starter are located in the accommodation space, and the starter is configured to start the turbine engine, the starter comprises a first electric motor.

A fracturing device includes a power unit, and the power unit includes a muffling compartment, a turbine engine, and an air intake unit. The air intake unit is communicated with the turbine engine through an intake pipe and configured to provide a combustion-supporting gas to the turbine engine; the air intake unit is at a top of the muffling compartment and the muffling compartment has an accommodation space, the turbine engine is within the accommodation space. A fan is further provided to generate wither positive pressure or negative presser in the muffling compartment to facilitate a cooling of the turbine engine.

A fracturing device includes a power unit, and the power unit includes a muffling compartment, a turbine engine, and an air intake unit. The air intake unit is communicated with the turbine engine through an intake pipe and configured to provide a combustion-supporting gas to the turbine engine; the air intake unit is at a top of the muffling compartment and the muffling compartment has an accommodation space, the turbine engine is within the accommodation space. A fan is further provided to generate wither positive pressure or negative presser in the muffling compartment to facilitate a cooling of the turbine engine.

A gas turbine engine article includes a ceramic body that defines a flange, first and second cooling passages partitioned from each other by the flange, a through-hole in the rib that connects the first and second cooling passages, a thermal insulation bushing that lines the through-hole.

A gas turbine engine article includes a ceramic body that defines a flange, first and second cooling passages partitioned from each other by the flange, a through-hole in the rib that connects the first and second cooling passages, a thermal insulation bushing that lines the through-hole.

Systems and methods for thermal washers are described herein. A thermal washer may comprise a first metallic plate having a first inner surface and a first outer surface, a second metallic plate having a second inner surface and a second outer surface, the second metallic plate being oriented substantially parallel to the first metallic plate such that the first inner surface and the second inner surface are separated by a gap, and a thermal wool in contact with the first inner surface and the second inner surface, the thermal wool filling a void between the first inner surface and the second inner surface. A width of the thermal wool may be substantially equal to a width of the first metallic plate and a length of the thermal wool may be substantially equal to a length of the first metallic plate.

Systems and methods for thermal seals are described herein. A thermal seal may comprise a first metallic plate having a first inner surface and a first outer surface, a second metallic plate having a second inner surface and a second outer surface, the second metallic plate being oriented substantially parallel to the first metallic plate such that the first inner surface and the second inner surface are separated by a gap, and a thermal wool having a plate portion in contact with the first inner surface and the second inner surface, the plate portion filling a void between the first inner surface and the second inner surface, and having a shoulder portion extending from a perimeter of the plate portion, the shoulder portion extending outward from between the first metallic plate and the second metallic plate.

This combustor is provided with an outer cylinder, an inner cylinder, a direct injection nozzle, a tail pipe, and a base end side acoustic attenuator. The outer cylinder is disposed inside a gas turbine casing. The inner cylinder is disposed on the inner circumferential side of the outer cylinder. The direct injection nozzle is disposed on the inner circumferential side of the inner cylinder. The tail pipe is connected to the inner cylinder, and fuel injected from the direct injection nozzle is burned on the inner circumferential side of the tail pipe. The base end side acoustic attenuator has an outer cylinder formation portion that is a part of a plate forming the outer cylinder, and an acoustic cover forming a base end side space in the gas turbine casing on the outer circumferential side of the outer cylinder in cooperation with the outer cylinder formation portion.