US1766886A - Gas-turbine unit - Google Patents

Gas-turbine unit Download PDF

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Publication number
US1766886A
US1766886A US753530A US75353024A US1766886A US 1766886 A US1766886 A US 1766886A US 753530 A US753530 A US 753530A US 75353024 A US75353024 A US 75353024A US 1766886 A US1766886 A US 1766886A
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United States
Prior art keywords
stages
gas
turbine
stage
engine
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Expired - Lifetime
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US753530A
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English (en)
Inventor
Elling Jens William Aegidius
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Individual
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Individual
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/003—Gas-turbine plants with heaters between turbine stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/36—Open cycles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the gasturbines of the impulse type hitherto known are based upon the same idea as 7 gas motors with pistons, viz. compression,
  • the present invention has ⁇ for its object to avoid completely the drawbacks which in the said respects have been'connected with the systems hitherto known and this is obtained'by adivisionof the process into two or more stages and by such an arrangement that .the work-of compression for the last stage independent of the preceedingstages.
  • the air is cooled at 9 and passes througha co uit 4 to a second compressor 2 forming e element of stage II ( Figure 2).
  • the air' is further compressed and is thencooled again at -9 and passed through "conduit 4 to a third compressor2 of stage 1 I Figure 1) in order to be finally compressed of stage t 'erein.
  • the I gas passes into a combustion chamber 3 into which a suitable combustible is sprayed at 10.
  • the products of combustion are now passed through the conduit 5 to the driving turbine 1 of stage I and from there through the conduit 5 into a combustion chamber 3?, into which a combustible is sprayed at 10*, and theythen pass through the turbine 1 of stage II.
  • the compressor 2 is coupled mechan- .ically to turbine 1 of stage'L-compressor 2 of stage II,yand compressor 2" to turbine 1 toturbine 1 of stageIII, and all these three stages are independent of'each other'in mechanical respect.
  • the curve 11-12 represents the usefulwork of compression.
  • the gross work of compression is represented by the curve 11-12', it being assumed that the work 11-12 be 75% of thework 11'-12' corresponding to an efliciency of 75% in the compressor.
  • the air from 2 has a temperature of 104 C. and is cooled at. 9 to a temperature of say 17 C. (12-13, Figure 6). Then it passes into compressor 2 and isfurt-her compressed corresponding to a rise in temperature from 17 to 104 C.
  • the curves 13-14 I and 13'-14 represent the corresponding as compared with the initial pressure (1 at to the temperature (310 'C.)
  • the engine 1 or 7 is not mechanically coupled to the aggregates of the stages I, II, III, but is mechanically quite independent thereof.
  • gearing between the engine, such as 1 or 7, and the driven machine such as 6, can be avoided.
  • the different stage sections need not be connected to one another in any other manner than through air pipes which connect the compressors in succeeding stages together and through gas pipes which connect the outlet from the turbine of one Stage with the combustion chamber for the turbine of the next stage.
  • a gas turbine unit comprising a series of mechanically independent means for compressing the gas in stages, means for adding ener of heat to the gas after compression, a series of means for expanding the compressed gas in stages down to an appropriate degree, each compressing means being mechanically coupled to one of the expanding means, an engine mechanically independent of said means for compressing and expanding the' gas, and means for conducting the degree, each compressing gas after final expansibnas a drivingfluid to the said independent engine.
  • a gas. turbine unit comprising compressors for gradually compressing the gas through a series of stages, said compressors being mechanically independent of one another, means for adding energy of heat to the gas after compression, turbines for expanding the so compressed gas through a series of stages down to an appropriate degree, said turbines being mechanicallyindependent of one another, means for coupling mechanically together the first compressor in the series of compression stages with the last turbine in the "series of expansion stages, means for coupling mechanically together the second compressor with the last but one turbine, and so on, a driving engine mechanically independent of said compressors and turbines, and means for conducting the so expanded gas as a driving fluid to said engine.
  • a gas turbine unit comprising a series of mechanically independent turbo compressors for compressing air in stages, means for ducting the gases after expansion in said ent engine.
  • A' gas turbi e unit comprising a. series of mechanicallygh iidependent means for compressing air in stages, means for cooling the gas between said stages, means for adding energy of heat to the air by combustion after the last compression, a series of means for ex-'' anding the compressed air and gases of comustion in stages down to an appropriate means being me stages asa driving fluid to the said independmeans, an engine led to one of the expanding mechanically independent of said compressing and expanding means,
  • a gas turbine unit comprising a series of mechanically independent means for com:
  • each compressing means being mechanically coupled to one of the expanding means, means for adding en ergy of heat to the air by combustion between two of t e expanding stages, an engine mechanica 1y independent of said comressmg and expanding means, and means or conducting the gases after expansion in said stages as a driving fluid to the said independent engine;

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US753530A 1923-12-13 1924-12-02 Gas-turbine unit Expired - Lifetime US1766886A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
NO1766886X 1923-12-13

Publications (1)

Publication Number Publication Date
US1766886A true US1766886A (en) 1930-06-24

Family

ID=19910422

Family Applications (1)

Application Number Title Priority Date Filing Date
US753530A Expired - Lifetime US1766886A (en) 1923-12-13 1924-12-02 Gas-turbine unit

Country Status (7)

Country Link
US (1) US1766886A (xx)
BE (1) BE331656A (xx)
CH (1) CH120074A (xx)
DE (1) DE529745C (xx)
FR (1) FR609387A (xx)
GB (1) GB268861A (xx)
NL (1) NL19660C (xx)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2428830A (en) * 1942-04-18 1947-10-14 Turbo Engineering Corp Regulation of combustion gas turbines arranged in series
US2526409A (en) * 1945-01-09 1950-10-17 Lockheed Aircraft Corp Turbo-propeller type power plant having radial flow exhaust turbine means
US2608822A (en) * 1944-10-07 1952-09-02 Turbolectric Corp Method of operation and regulation of thermal power plants
EP0699272A1 (en) * 1993-04-23 1996-03-06 Cascaded Advanced Turbine Limited Partnership High efficiency multi-shaft reheat turbine with intercooling and recuperation

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2428830A (en) * 1942-04-18 1947-10-14 Turbo Engineering Corp Regulation of combustion gas turbines arranged in series
US2608822A (en) * 1944-10-07 1952-09-02 Turbolectric Corp Method of operation and regulation of thermal power plants
US2526409A (en) * 1945-01-09 1950-10-17 Lockheed Aircraft Corp Turbo-propeller type power plant having radial flow exhaust turbine means
EP0699272A1 (en) * 1993-04-23 1996-03-06 Cascaded Advanced Turbine Limited Partnership High efficiency multi-shaft reheat turbine with intercooling and recuperation
EP0699272A4 (en) * 1993-04-23 1997-01-22 Cascaded Advanced Turbine HIGH-EFFICIENCY MULTI-SHAFT TURBINE WITH HEATER, INTERCOOLER AND RECOVERY

Also Published As

Publication number Publication date
GB268861A (en) 1927-04-05
FR609387A (fr) 1926-08-13
NL19660C (xx)
DE529745C (de) 1931-07-16
CH120074A (de) 1927-05-02
BE331656A (xx)

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