A seal gas supply control method according to the present invention comprises a step for detecting a pressure difference between an internal pressure of a rotary machine and a supply pressure of a seal gas with respect to a dry gas seal portion, a step for adjusting an opening degree of a seal gas supply valve on the basis of the detected pressure difference between the internal pressure and the supply pressure, and a step for detecting a vent pressure for discharging the seal gas evacuated from the dry gas seal portion to the outside. The seal gas supply control method fully opens the seal gas supply valve when the detected vent pressure satisfies a predetermined condition.

A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.

A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.

A gas turbine engine configured to combust, by means of a combustor, a compressed air obtained through compression by a compressor, and drive a turbine with use of high-temperature and high-pressure combustion gas generated by the combustion, the gas turbine engine including: a plurality of air passages through which different portions in the gas turbine engine communicate with one another; and a switching device configured to switch air flow paths between the plurality of air passages, wherein the plurality of air passages are each formed by an air pipe disposed outside a compressor casing, and the switching device is mounted to an outer surface of the compressor casing via a heat insulation member.

There is disclosed a controlled gap seal for a gas turbine engine including a ring configured to be in a sealing engagement with a housing and a runner configured for rotation relative to the ring about the central axis. The runner has a runner face facing a ring face of the ring. The ring face is spaced apart from the runner face by a gap. A plurality of surface discontinuities are circumferentially distributed around the central axis on the runner face and/or the ring face. The plurality of surface discontinuities are spaced relative to one another such that a first set of adjacent surface discontinuities are circumferentially spaced from each other at a different distance than a second set of adjacent surface discontinuities. A method of using the controlled gap seal is disclosed.

Disclosed herein is a sealing gas supply apparatus. In the sealing gas supply apparatus for supplying sealing gas to a turbomachine of a power generation system, a source comprises at least one low-temperature source for supplying a working fluid to the sealing gas supply apparatus and at least one high-temperature source for supplying a working fluid having a higher temperature than the low-temperature source to the sealing gas supply apparatus, and the working fluids are mixed in the sealing gas supply apparatus to be suitable for a sealing condition as a temperature condition required in a sealing system so as to be supplied to the sealing system of the turbomachine. In accordance with the present disclosure, since separate electric power is not consumed during normal operation by improving a turbine sealing gas source, it is possible to enhance power generation performance by a reduction in power consumption.

Disclosed herein is a sealing gas supply apparatus. In the sealing gas supply apparatus for supplying sealing gas to a turbomachine of a power generation system, a source comprises at least one low-temperature source for supplying a working fluid to the sealing gas supply apparatus and at least one high-temperature source for supplying a working fluid having a higher temperature than the low-temperature source to the sealing gas supply apparatus, and the working fluids are mixed in the sealing gas supply apparatus to be suitable for a sealing condition as a temperature condition required in a sealing system so as to be supplied to the sealing system of the turbomachine. In accordance with the present disclosure, since separate electric power is not consumed during normal operation by improving a turbine sealing gas source, it is possible to enhance power generation performance by a reduction in power consumption.

A method for checking a steam turbine, wherein a first operating variable and a second operating variable are determined, wherein a correlation between the first and second operating variable prevails, and a confidence band having an upper maximum value and a lower minimum value is created, wherein a notification is generated as long as the second operating variable is outside the confidence band during operation.

A method for checking a steam turbine, wherein a first operating variable and a second operating variable are determined, wherein a correlation between the first and second operating variable prevails, and a confidence band having an upper maximum value and a lower minimum value is created, wherein a notification is generated as long as the second operating variable is outside the confidence band during operation.

A gas turbine engine includes a fan, a compressor section, and a turbine section configured to drive the compressor section and the fan. A buffer system is configured to communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine. A method and a buffer system are also disclosed.