US1775527A - Multistage gas turbine - Google Patents

Multistage gas turbine Download PDF

Info

Publication number
US1775527A
US1775527A US129740A US12974026A US1775527A US 1775527 A US1775527 A US 1775527A US 129740 A US129740 A US 129740A US 12974026 A US12974026 A US 12974026A US 1775527 A US1775527 A US 1775527A
Authority
US
United States
Prior art keywords
turbine
steam
nozzles
rotor
combustion gases
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US129740A
Other languages
English (en)
Inventor
Holzwarth Hans
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
HOLZWARTH GAS TURBINE CO
Original Assignee
HOLZWARTH GAS TURBINE CO
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to BE343703D priority Critical patent/BE343703A/xx
Application filed by HOLZWARTH GAS TURBINE CO filed Critical HOLZWARTH GAS TURBINE CO
Priority to US129740A priority patent/US1775527A/en
Application granted granted Critical
Publication of US1775527A publication Critical patent/US1775527A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
    • F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
    • F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
    • F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle

Definitions

  • My present invention relates to a power plant in which combustion gases obtained by the explosion of a mixture of fuel and air are employed to o erate the rotor of a turbine in conjunctionkwlth steam, and in which the remaining ener of the steam and of the combustion gases 1s utilized in an efiicient way for the production of additional power.
  • Fig. 1 is an elevation of the plant with parts in section along the line 1-1 of Figs. 2 and 3, duplicates in elevation ll of parts appearing in section being omitted for the sake of clearness;
  • Fig. 2 is a cross-section on line 2-2 of Fig. 1; and Fig.
  • FIG. 3 is a section along the line 3-3 of Fig. 1.
  • the engine may have one chamber of this character or a plurality of them.
  • Suitable inlet valves are provided for the admission of air and fuel respectively and an outlet 15 valve 1 is provided 1n conjunction with such explosion chamber, said outlet valve being arranged in a ring 2 interposed between the combustion chamber or cliambersand the high pressure rotor 3 and provided with one or 80 more nozzles 4 to discharge the successive 'jets of combustion gases resulting from the successive explosions against the blades of said rotor.
  • Any suitable mechanism is provided for operating the inlet and outlet valves at the proper times and for igniting or exploding the combustible mixture.
  • the combustion gases After issuing from the nozzles 4, the combustion gases, as they issue from the blade channels of the rotor 3. are received in an exhaust chamher 5 which is in direct communication with the inlet of an intermediate pressure turbine 6 of any suitable construction, but preferably of the multi-stage type which embodies a suc O cession of rotor rings alternating with stator rings.
  • an intermediate pressure turbine 6 At the outlet end of thev intermediate pressure turbine 6, the combustion gases pass out through a pipe 7 and give off part of their heat to a boiler 7 whereupon they escape to the atmosphere.
  • a boiler 7 high pressure steam is generated and superheated and will be understood from Fig. 2 showing the line 1-1- along which the section shown in Fig. 1 is taken.
  • the catch nozzles take up the jets of steam issuing from the nozzle conduits 10', and are not entered by combustion gases; It will be seen that the arrangement is such that combustion gases from the exhaust chamber 5 and the steam from the catch nozzles 10 will be kept separate from each other during their passage through the intermediate pressure turbine 6. The steam will at this point also exert a cooling action on the turbine blades since the combustion gases passing through the intermediate turbine, while not so hot when they were at the high temperature turbine, are still of a temperature above that of the steam.
  • each nozzle 9 has a catch nozzle 10 and a catch nozzle 12 and also a charging nozzle 13 associated therewith, only one such set of nozzles being shown in Fig.1 to avoid complicating the drawing.
  • a cooling packet 11 surrounding the exhaust chamber 5 and the casing of the intermediate pressure turbine 6. Any suitable cooling medium may be passed through said jacket.
  • the drawing shows only the nozzle 12 and the pipe 13 which are in alignment with ,the catch nozzle 10 illustrated, although two such nozzles 12 and pipes 13 are provided in correspondence with the two catch nozzles 10 that cooperate with the two steam nozzles 9. It will be seen that the high pressure turbine and the intermediate pressure turbine are driven both by steam and by combustion gases, while the low pressure turbine is driven by steam alone.
  • the gas em loyed as fuel contains 500 thermal units a1.) .per cubic meter at the temperature of 0 C. and atmospheric pressure.
  • the pressure of the combustion gases at the point of their admissionto the explosion chamber 1 may be 6 atmospheres and their temperature 7 5 C.
  • the maximum pressure which the combustion gases reach during explosion may be 35.4 atmospheres absolute and their temperature 17 00 C.
  • the combustion gases may have a pressure of 5.25 atmospheres .absolute and a temperature of 1110 C., the eificiency of this high pressure stage, so far as the combustion gases are concerned, being 70%, the speed of the combustion gases entering the high pressure stage about 880 meters er second, and the effective thermal drop equivalent to 89 Cal. per cubic meter.
  • the exhaust gases from the chamber 5 enter the intermediate pressure turbine at a pressure of 5.25 atmospheres absolute and a" temperature of 1110 C. and leave the same at a pressure of 1.06 atmospheres and a temperature of about 725. The efliciency of the intermediate pressure stage, so far as the.
  • combustion gases are concerned, is about 82% and the-thermal drop equivalent to 138 Cal. per cubic meter.
  • steam the
  • pressure of the steam delivered to the nozzles 9 may be 17 atmospheres absolute and its temperature 400 C.
  • the pressure of the steam is 5.25 atmospheres absolute.
  • the efliciency of the high pressure stage, so far as steam is concerned, is The final temperature is 350 C. and the drop equivalent to 12 Cal. per cubic meter of fuel gas.
  • the inlet pressure of the stage is 5.25 atmospheres and its temperature 300 C. Its outlet pressure is 1.06 atmospheres absolute and its outlet temperature 450 C.
  • the efficiency is 82% and the drop 15 Cal. per. cubic meter.
  • the'steam is admitted with 1 atmosphere absolute and a temperature of 450 C. and exhausts to'the condenser at a temperature of 155 C.
  • the total effective thermal drop of steam from the high pressure stage to the condenser is 65 Cal. per cubic meter of fuel gas.
  • a multistage gas turbine plant comprising an explosion chamber for the generation of combustion gases, a high pressure rotor operated by said gases, an exhaust chamber into which said gases issue from said. rotor, an intermediate pressure turbine the inlet of which communicates directly with said chamber, steam nozzles arranged to discharge steam against said rotor, catch nozzles located in said exhaust chamber and arranged to receive the steam after its passage through said rotor. discharge nozzles likewise arranged in said chamber and delivering steam to said intermediate pressure turbine, conduits arranged wholly in said exhaust chamber for conveying the steam from said catch nozzles to said discharge nozzles, means for collecting separately the combustion gases and the steam issuing from said intermediate pressure turbine, a low pressure condensing turbine actuated by the steam thus collected, a
  • a multistage turbine plant comprising a high pressure explosion turbine having means including an explosion chamber, for discharging separately successive jets of combustion gases and another driving fluid no against its rotor, an exhaust chamber into which said gases issue from said rotor, another turbine the inlet of which receives said gases from said exhaust chamber, catch nozzles arranged in said exhaust chamber to re 95 eive the other driving fluid as it issues from the high'pressure rotor, discharge nozzles arranged to deliver said second fluid to the second turbine, and conduit's'extending from said catch nozzles to said discharge nozzles [00 iand arranged wholly in said exhaust cham- 4;.
  • a multistage turbine plant comprising a high pressure explosion turbine having means including an explosion chamber, for 105 discharging separately successive jets of combustion gases and another drivingfluid against its rotor, an exhaust chamber into Which said gases issue from said rotor, an
  • catch nozzles arranged to receive said other driving fluid as it issues from said intermediate turbine, a third turbine, discharge nozzles arranged to deliver said other driving fluid to said third turbine, and a conduit connecting said last mentioned catch and discharge nozzles and located in the exhaust chamber of said intermediate turbine, Whereby said other driving fluid travels in heatexchange relation with the gases exhaust 39

Landscapes

  • 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)
US129740A 1926-08-17 1926-08-17 Multistage gas turbine Expired - Lifetime US1775527A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
BE343703D BE343703A (en, 2012) 1926-08-17
US129740A US1775527A (en) 1926-08-17 1926-08-17 Multistage gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US129740A US1775527A (en) 1926-08-17 1926-08-17 Multistage gas turbine

Publications (1)

Publication Number Publication Date
US1775527A true US1775527A (en) 1930-09-09

Family

ID=22441377

Family Applications (1)

Application Number Title Priority Date Filing Date
US129740A Expired - Lifetime US1775527A (en) 1926-08-17 1926-08-17 Multistage gas turbine

Country Status (2)

Country Link
US (1) US1775527A (en, 2012)
BE (1) BE343703A (en, 2012)

Also Published As

Publication number Publication date
BE343703A (en, 2012)

Similar Documents

Publication Publication Date Title
US3315467A (en) Reheat gas turbine power plant with air admission to the primary combustion zone of the reheat combustion chamber structure
US2428136A (en) Combustion gas and waste heat steam turbine
EP0173774A1 (en) Gas turbine engine
US2298663A (en) Gas turbine plant
US2930190A (en) Bypass gas turbine power plant employing regenerative cycle
US2553867A (en) Power plant
US2159758A (en) Power plant
US2242767A (en) Gas turbine plant
GB1284335A (en) Improvements in or relating to gas turbine engines
US2312995A (en) Gas turbine plant
US2131781A (en) Gas turbine system of the continuous combustion type
US2305785A (en) Working process and mechanical equipment for gas turbines
US1901873A (en) Multistage constant volume explosion process and apparatus
US2631430A (en) Gas turbine power plant having coaxially arranged combustors and regenerator
US1775527A (en) Multistage gas turbine
US2466723A (en) Steam and gas power generating plant
US2660858A (en) Air-cooling gas turbine blade
US1982664A (en) Compound gas turbine and method of producing power therewith
US4137706A (en) Engine in which fuel is reacted in a plurality of stages
US1970747A (en) Power plant
US1278499A (en) Internal-combustion turbine.
US2464861A (en) Hot-air turbine power plant
US1951360A (en) Portable power plant for vehicles
US1829749A (en) Combined steam and combustion gas power plant
US1948539A (en) Steam generator