Gas turbine and gas turbine cooling method
First Claim
1. A gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path, wherein a plurality of engagement portions between said sealing means and said nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and downstream one of said plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft.
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Accused Products
Abstract
A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.
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Citations
11 Claims
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1. A gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path,
wherein a plurality of engagement portions between said sealing means and said nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and downstream one of said plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft.
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2. A gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path,
wherein a plurality of engagement portions between said sealing means and said nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, upstream one of said plurality of engagement portions has a contact interface formed in a circumferential direction of a circle about a turbine rotary shaft, and the downstream-side engagement portion has a contact interface formed in a direction across the turbine rotary shaft.
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3. A gas turbine comprising a compressor for producing compressed air, a combustor for mixing and burning the compressed air and fuel, and a turbine rotated by combustion gases exiting said combustor, said turbine including a gas path formed therein between a casing and a turbine rotor for passage of the combustion gases, a nozzle vane and a diaphragm engaging with said diaphragm which are disposed in a channel of the downward flowing combustion gases on the outlet side of said gas path, an upstream-side wheel space and a downstream-side wheel space formed between said diaphragm and corresponding rotor blades, and holes formed in upstream- and downstream-side lateral walls of said diaphragm for communication with said upstream-side wheel space and said downstream-side wheel space to supply a coolant in said diaphragm to said upstream-side wheel space and said downstream-side wheel space,
wherein said turbine further includes a plurality of engagement portions between said diaphragm and said nozzle vane, which are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, a nozzle vane hook and a diaphragm hook arranged to provide upstream one of said plurality of engagement portions with a contact interface thereof formed in a circumferential direction of a circle about a turbine rotary shaft, and a nozzle vane hook and a diaphragm hook arranged to provide a downstream one of said plurality of engagement portions with a contact interface thereof formed in a direction across the turbine rotary shaft, wherein the downstream-side engagement portion having a lower surface of said nozzle vane hook and an upper surface of said diaphragm hook being held in contact with each other.
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10. A method of cooling a gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path, said nozzle vane and said sealing means cooperatively defining a cavity, wherein said method comprises the steps of:
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providing a plurality of engagement portions between said sealing means and said nozzle vane successively from the upstream side toward the downstream side in a direction of flow of the combustion gases;
forming downstream one of said plurality of engagement portions to provide surface contact in a direction across a turbine rotary shaft; and
supplying a coolant introduced through the inside of said nozzle vane to said cavity and causing the coolant to flow toward the side upstream of said sealing means.
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11. A method of cooling a gas turbine including a nozzle vane and sealing means engaging with said nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel, said nozzle vane and said sealing means being disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path, said nozzle vane and said sealing means cooperatively defining a cavity, wherein said method comprises the steps of:
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providing a plurality of engagement portions between said sealing means and said nozzle vane successively from the upstream side toward the downstream side in a direction of flow of the combustion gases;
forming upstream one of said plurality of engagement portions to provide surface contact in a circumferential direction of a circle about a turbine rotary shaft, forming downstream one of said plurality of engagement portions to provide surface contact in a direction across said turbine rotary shaft; and
supplying a coolant introduced through the inside of said nozzle vane to said cavity and causing the coolant to flow toward the side upstream of said sealing means.
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Specification