Patent US5360318A successfully refreshed from Google Patents.
US5360318A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Compressor for gas turbine and gas turbine
Assignee: Hitachi Ltd
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Filing: 1993-08-06
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Granted: 1994-11-01
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Expires: 2013-08-06
Abstract
Abstract A high-temperature gas turbine includes a compressor, and a turbine coupled to the compressor, the turbine being capable of rotating at a high speed by a gas of firing temperature generated by a combustor. The compressor includes a combined type rotor shaft and blades of at least 15 stages which are implanted in the combined type rotor shaft. The compressor compresses air to a temperature of 400 DEG C. or above. The combined type rotor shaft is made of Ni-Cr-Mo-V low alloy steel having all bainitic microstructure whose composition consists, as analyzed in weight percent, of 0.15-0.40% C, 0.1% or less Si, 0.5% or less Mn, 1.5-2.5% Ni, 0.8-2.5% Cr, 0.8-2.0% Mo, 0.1-0.35% V and the balance substantially of Fe.
Inventors
- 👤 Masao Siga
- 👤 Hajime Toriya
- 👤 Yutaka Fukui
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 16:21
CPC Classifications
F; F04; F04D; F04D29/00; F04D29/05; F04D29/053; C; C22; C22C; C22C38/00; C22C38/18; C22C38/40; C22C38/44; C22C38/46; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F01D5/085; F01D5/12; F01D5/28; F04D29/02; F04D29/023; F05; F05D; F05D2300/00; F05D2300/10; F05D2300/17; F05D2300/171; F05D2300/60; F05D2300/608; Y; Y02; Y02E; Y02E20/00; Y02E20/16
Claims Analysis
Total Claims: 21
Claim 1
Independent Claim
103 words
A high-temperature gas turbine including a compressor for compressing air, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine rotated at a high speed by said combustion gas, said compressor has a monolithic rotor shaft and blades of at least fifteen stages which are implanted in said monolithic rotor shaft, a temperature of the compressed air is at least 400° C., a compression ratio is between 15 and 20, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 2
Dependent Claim
103 words
A high-temperature gas turbine including a compressor for compressing air, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine rotated at a high speed by said combustion gas, said compressor has a monolithic rotor shaft and blades of at least fifteen stages which are implanted in said monolithic rotor shaft, a temperature of the compressed air is at least 400° C., a compression ratio is between 15 and 20, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 3
Dependent Claim
150 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor and a combustor for generating a combustion gas, said gas turbine being rotated at a high speed by the combustion gas, wherein said compressor has a monolithic rotor shaft and blades of at least fifteen stages implanted in said rotor shaft, said rotor shaft being made of a Ni--Cr--Mo--V low alloy steel, a 50% fracture appearance transition temperature thereof is not greater than 20° C. and a 10 5 hours creep rupture strength under 475° C. is not less than 30 kg/mm 2 , a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or thereabove, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 4
Dependent Claim
150 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor and a combustor for generating a combustion gas, said gas turbine being rotated at a high speed by the combustion gas, wherein said compressor has a monolithic rotor shaft and blades of at least fifteen stages implanted in said rotor shaft, said rotor shaft being made of a Ni--Cr--Mo--V low alloy steel, a 50% fracture appearance transition temperature thereof is not greater than 20° C. and a 10 5 hours creep rupture strength under 475° C. is not less than 30 kg/mm 2 , a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or thereabove, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 5
Dependent Claim
102 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine rotated at a high speed by the combustion gas, wherein said compressor has a combined type rotor shaft and blades implanted in said rotor shaft, said rotor shaft being made of a Ni--Cr--Mo--V type low alloy steel having substantially in whole bainite microstructure which comprises, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35 and the balance substantially of Fe.
Claim 6
Dependent Claim
102 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine rotated at a high speed by the combustion gas, wherein said compressor has a combined type rotor shaft and blades implanted in said rotor shaft, said rotor shaft being made of a Ni--Cr--Mo--V type low alloy steel having substantially in whole bainite microstructure which comprises, in weight percent, C of 0.15-0.40%, Si not more than 0.1%, Mn not more than 0.5%, Ni of 1.5-2.5%, Cr of 0.8-2.5%, Mo of 0.8-2.0%, V of 0.1-0.35 and the balance substantially of Fe.
Claim 7
Dependent Claim
27 words
A high-temperature gas turbine according to claim 3, wherein said low alloy steel further comprises 0.01-0.1% of at least one of Nb and Ta, in weight percent.
Claim 8
Dependent Claim
78 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a combined type rotor shaft made of a Ni--Cr--Mo--V type low alloy steel and blades implanted in said rotor shaft, a ratio of a maximum diameter (D) of said rotor shaft to a length (L) thereof between a first stage and a last stage of the blades is 0.40-0.55.
Claim 9
Dependent Claim
78 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a combined type rotor shaft made of a Ni--Cr--Mo--V type low alloy steel and blades implanted in said rotor shaft, a ratio of a maximum diameter (D) of said rotor shaft to a length (L) thereof between a first stage and a last stage of the blades is 0.40-0.55.
Claim 10
Dependent Claim
118 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in a ring-shaped groove extending on an entire peripheral surface of said rotor shaft, a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 11
Dependent Claim
118 words
A high-temperature gas turbine including a compressor, a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in a ring-shaped groove extending on an entire peripheral surface of said rotor shaft, a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 12
Dependent Claim
193 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in said monolithic rotor shaft, the blade at a first stage and, as required, at least one stage between a second stage and a fifth stage is inserted separately into the rotor shaft in an axial direction thereof while the blades at the remaining stages from the second stage to a last stage with excluding the blade inserted in the axial direction excluding the blade inserted in the axial direction are implanted in a ring-shaped a ring-shaped groove extending over an entire peripheral surface of said rotor shaft, a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 13
Dependent Claim
193 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in said monolithic rotor shaft, the blade at a first stage and, as required, at least one stage between a second stage and a fifth stage is inserted separately into the rotor shaft in an axial direction thereof while the blades at the remaining stages from the second stage to a last stage with excluding the blade inserted in the axial direction excluding the blade inserted in the axial direction are implanted in a ring-shaped a ring-shaped groove extending over an entire peripheral surface of said rotor shaft, a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 14
Dependent Claim
169 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in said rotor shaft, the blade of a first stage and, as required, at least one stage between a second stage and a fifth stage being made of a titanium alloy while the blades at the remaining stages from the second stage to a last stage, including the stage with the blade made of titanium alloy, being made of martensitic stainless steel, and wherein a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 15
Dependent Claim
169 words
A high-temperature gas turbine including a compressor, and a turbine coupled to said compressor, said turbine rotated at a high speed by a combustion gas, wherein said compressor has a monolithic rotor shaft made of Ni--Cr--Mo--V low alloy steel with bainite structure and blades of at least fifteen stages which are implanted in said rotor shaft, the blade of a first stage and, as required, at least one stage between a second stage and a fifth stage being made of a titanium alloy while the blades at the remaining stages from the second stage to a last stage, including the stage with the blade made of titanium alloy, being made of martensitic stainless steel, and wherein a compression ratio of the air compressed by the compressor is between 15 and 20, a temperature of the compressed air is 400° C. or greater, a temperature of the combustion gas at a combustion outlet is 1400° C. or greater, and a thermal efficiency of the gas turbine is 35% or greater.
Claim 16
Dependent Claim
69 words
A compressor for a gas turbine, having a combined type rotor shaft and blades implanted therein at multi-stages, wherein said rotor shaft is made of a Ni--Cr--Mo--V type low alloy steel having substantially in whole bainite microstructure whose composition comprises, in weight percent, 0.15-0.40% C, Si not more than 0.1%, Mn not more than 0.5%, 1.5-2.5% Ni, 0.8-2.5% Cr, 0.8-2.0% Mo, 0.1-0.35% V and the balance substantially of Fe.
Claim 17
Dependent Claim
69 words
A compressor for a gas turbine, having a combined type rotor shaft and blades implanted therein at multi-stages, wherein said rotor shaft is made of a Ni--Cr--Mo--V type low alloy steel having substantially in whole bainite microstructure whose composition comprises, in weight percent, 0.15-0.40% C, Si not more than 0.1%, Mn not more than 0.5%, 1.5-2.5% Ni, 0.8-2.5% Cr, 0.8-2.0% Mo, 0.1-0.35% V and the balance substantially of Fe.
Claim 18
Dependent Claim
46 words
A rotor shaft for a gas turbine compressor, having substantially in whole bainite microstructure whose composition comprises, in weight percent, 0.15-0.40% C, Si not more than 0.1%, Mn not more than 0.5%, 1.5-2.5% Ni, 0.8-2.5% Cr, 0.8-2.0% Mo, 0.1-0.35% V and the balance substantially of Fe.
Claim 19
Dependent Claim
46 words
A rotor shaft for a gas turbine compressor, having substantially in whole bainite microstructure whose composition comprises, in weight percent, 0.15-0.40% C, Si not more than 0.1%, Mn not more than 0.5%, 1.5-2.5% Ni, 0.8-2.5% Cr, 0.8-2.0% Mo, 0.1-0.35% V and the balance substantially of Fe.
Claim 20
Dependent Claim
111 words
A high-temperature gas turbine including a compressor for compressing air, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine being rotated at a high speed by said combustion gas, wherein said combustor has a monolithic rotor shaft and blades of at least twelve stages which are implanted in said monolithic rotor shaft, and a temperature of the compressed air is at least 400° C., said rotor shaft is made of Ni--Cr--Mo--V low alloy steel, a 50% fracture appearance transition thereof is not more than 20° and a 10 5 hours creep rupture strength under 475° C. is not less than 30 kg/mm 2 .
Claim 21
Dependent Claim
111 words
A high-temperature gas turbine including a compressor for compressing air, a turbine coupled to said compressor and a combustor for generating a combustion gas, said turbine being rotated at a high speed by said combustion gas, wherein said combustor has a monolithic rotor shaft and blades of at least twelve stages which are implanted in said monolithic rotor shaft, and a temperature of the compressed air is at least 400° C., said rotor shaft is made of Ni--Cr--Mo--V low alloy steel, a 50% fracture appearance transition thereof is not more than 20° and a 10 5 hours creep rupture strength under 475° C. is not less than 30 kg/mm 2 .
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
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| 3.5 Years (Year 4) | 1997-10-31 | 1998-05-02 | 1998-11-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-10-31 | 2002-05-02 | 2002-11-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-10-31 | 2006-05-02 | 2006-11-01 | $7700.00 | Window Closed / Lapsed |