WO2011112108A2 - Bullgear gas turbine with intercooler and reheat - Google Patents

Bullgear gas turbine with intercooler and reheat Download PDF

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Publication number
WO2011112108A2
WO2011112108A2 PCT/RO2010/000009 RO2010000009W WO2011112108A2 WO 2011112108 A2 WO2011112108 A2 WO 2011112108A2 RO 2010000009 W RO2010000009 W RO 2010000009W WO 2011112108 A2 WO2011112108 A2 WO 2011112108A2
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WO
WIPO (PCT)
Prior art keywords
bullgear
intercooler
compressor
compressors
reheat
Prior art date
Application number
PCT/RO2010/000009
Other languages
French (fr)
Other versions
WO2011112108A3 (en
Inventor
Valentin Silivestru
Romulus Petcu
Cristian CÎRLĂNESCU
Jeni Alina Popescu
Valeriu Alexandru Vilag
Original Assignee
Institutul Naţional De Cercetare - Dezvoltare Turbomotoare Comoti
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Publication date
Application filed by Institutul Naţional De Cercetare - Dezvoltare Turbomotoare Comoti filed Critical Institutul Naţional De Cercetare - Dezvoltare Turbomotoare Comoti
Publication of WO2011112108A2 publication Critical patent/WO2011112108A2/en
Publication of WO2011112108A3 publication Critical patent/WO2011112108A3/en

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Classifications

    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D13/00—Combinations of two or more machines or engines
    • F01D13/02—Working-fluid interconnection of machines or engines
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
    • 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
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/74—Application in combination with a gas turbine

Definitions

  • the invention refers to a bullgear gas turbine with intercooler and rehea which can be used for driving a payload and/or as burned gases generator.
  • the technical problem solved by the invention consist in the fact that by using a working fluid and accomplishing a highly efficient thermodynamic cycle, with subsequent and multiple compressions, expansions, intercooling and reheating a burned gases flow and/or the mechanical energy necessary for driving a payload are created.
  • the bullgear gas turbine with intercooler and reheat eliminates the previous disadvantages by consisting in a succession of compressors (14,16,18,20,22), combustion chambers (23,25,27,29,31) and turbines (24,26,28,30,32), the succession of compressors (14,16,18,20,22) each driven by an appointed turbine (24,26,28,30,32) through appointed shafts (8,9,10,11,12) each fitted with a pinion (3,4,5,6,7), each pinion having a different number of dents driving the bullgear (1) and therefore ensuring different speeds for each turbo-compressor group (14-24,16-25,18-27,20-29,22-31), the bullgear (1) driving in its turn, through a central shaft (2) and a coupling (34), a payload (33), and the first compressor (14) is preceded by an aspiration filter (13), each of the following compressors (16,18,20,22) are preceded by a inter
  • the total power of the bullgear gas turbine with intercooler and reheat is divided (into) to several stages and results from the differences between the power consumed by the compressors and the installed power of the turbines for each turbo-compressor group;
  • thermodynamic cycle The efficiency of the thermodynamic cycle is closer to the efficiency of the Carnot cycle;
  • Each turbo-compressor group is working at its own optimum speed which can be different from the others';
  • the bullgear gas turbine with intercooler and reheat has an extended life cycle.
  • An example of implementation is presented hereinafter along with the figures representing: Fig. 1, the thermo-mechanic diagram of the bullgear gas turbine with intercooler and reheat;
  • Fig. 2 the transmission diagram of the bullgear gas turbine with intercooler and reheat
  • Fig. 3 the thermodynamic cycle of the bullgear gas turbine with intercooler and reheat in enthalpy-entropy coordinates.
  • the bullgear gas turbine with intercooler and reheat includes several turbo-compressor groups, each integrating the compressors (14,16,18,20,22), the shafts (8,9,10,11,12), the pinions (3,4,5,6,7) and the turbines (24,26,28,30,32).
  • the intercoolers 15,17,19,21
  • each turbine 24,26,28,30,32
  • the combustion chambers 23,25,27,29,31.
  • the pinions (3,4,5,6,7) of each group interlocks at different speeds (nl,n2,n3,n4,n5) with the bullgear (1) having the speed (n) and delivering the power through the shaft (2) and the coupling (34) to the payload (33).
  • the atmospheric air is admitted through the aspiration filter (13), passes the compressor (14) and is then delivered to the intercooler (15) and continues the layout through the compressors (16,18,20,22) with the intercoolers (17,19,21).
  • the compressed air is sent into the combustion chamber (23), where the fuel (35) is injected, and then delivered to the turbine (24) following then the layout through the combustion chambers (25,27,29,31), with the fuel injections (36,37,38,39), with the appointed turbines (26,28,30,32) being then exhausted into the atmosphere as burned gases.
  • the thermodynamic cycle accomplished by the gas turbine is represented in enthalpy-entropy coordinates and includes the compressions (101,103,105,107,109) with the intercooling (102,104,106,108), the combustion (110) and expansions (111,113,115,117,119) with the reheating (112,114,116,118).
  • the bullgear gas turbine with intercooling and reheat may integrate as many stages of compressions, intercooling, intermediary combustions and expansions, the efficiency increasing with the number of the stages.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

The invention refers to a bullgear gas turbine with intercooler and reheat, which can be used for driving a payload and/or as burned gases generator. The bullgear gas turbine with intercooler and reheat integrates several turbo-compressor groups each including the compressors (14,16,18,20,22), the shafts (8,9,10,11,12), the pinions (3, 4, 5, 6, 7) and the turbines (24,26,28,30,32). In front of each compressor (16,18, 20, 22) there are placed the intercoolers (15,17,19,21) and in front of each turbine (24,26,28,30,32) there are the combustion chambers (23, 25, 27, 29, 31). The pinions (3,4,5,6,7) of each turbo-compressor group interlock at different speeds (n1, n2, n3, n4, n5) with the bullgear (1) having the speed (n) and delivering the power through the shaft (2) and the coupling (34) to the payload (33). The atmospheric air is admitted through the aspiration filter (13), passes through the compressor (14) and is then delivered to the intercooler (15) and continues its layout through the compressors (16,18, 20, 22) with the intercoolers (17,19, 21). The compressed air is sent into the combustion chamber (23), where the fuel (35) is injected, and then delivered to the turbine (24) following then the layout through the combustion chambers (25, 27, 29, 31), which have the fuel injections (36,37,38,39), with the appointed turbines (26, 28, 30, 32) resulting burned gases exhausted into the atmosphere.

Description

BULLGEAR GAS TURBINE WITH INTERCOOLER AND REHEAT
The invention refers to a bullgear gas turbine with intercooler and rehea which can be used for driving a payload and/or as burned gases generator.
There are known a system and a method for combustor - turbine and compressor units integration according to EP 0512568A1.
It is also known a power generator system based on residual heat according to US4473754A.
The disadvantages of these systems consist in the fact that the entire power is transmitted to the bullgear through a single pinion to which the denture is highly stressed due to the placement of the turbine or turbines on the same shaft.
The technical problem solved by the invention consist in the fact that by using a working fluid and accomplishing a highly efficient thermodynamic cycle, with subsequent and multiple compressions, expansions, intercooling and reheating a burned gases flow and/or the mechanical energy necessary for driving a payload are created.
The bullgear gas turbine with intercooler and reheat, according to the invention, eliminates the previous disadvantages by consisting in a succession of compressors (14,16,18,20,22), combustion chambers (23,25,27,29,31) and turbines (24,26,28,30,32), the succession of compressors (14,16,18,20,22) each driven by an appointed turbine (24,26,28,30,32) through appointed shafts (8,9,10,11,12) each fitted with a pinion (3,4,5,6,7), each pinion having a different number of dents driving the bullgear (1) and therefore ensuring different speeds for each turbo-compressor group (14-24,16-25,18-27,20-29,22-31), the bullgear (1) driving in its turn, through a central shaft (2) and a coupling (34), a payload (33), and the first compressor (14) is preceded by an aspiration filter (13), each of the following compressors (16,18,20,22) are preceded by a intercooler (15,17,19,21), each turbine (24,26,28,30,32) is preceded by a combustion chamber (23,25,27,29,31) with fuel injection and in the working cycle the air enters through the aspiration filter (13) into the first compressor (14) and is then cooled by the intercoolers (15,17,19,21) prior to entering each of the compressors (16,18,20,22), is then mixed with the fuel and burned in each of the combustion chambers (23,25,27,29,31) placed before each of the turbines (24,26,28,30,32) resulting the necessary energy to drive each turbine (24,26,28,30,32) which is distributed to each compressor (14,16,18,20,22) and the excedent is delivered through the shafts (8,9,10,11,12) and the pinions (3,4,5,6,7) to the bullgear (1) and hence to the payload (33).
The invention presents the following advantages:
The total power of the bullgear gas turbine with intercooler and reheat is divided (into) to several stages and results from the differences between the power consumed by the compressors and the installed power of the turbines for each turbo-compressor group;
The efficiency of the thermodynamic cycle is closer to the efficiency of the Carnot cycle; Each turbo-compressor group is working at its own optimum speed which can be different from the others';
The dentures of the pinions interlocking with the bullgear are less stressed;
The bullgear gas turbine with intercooler and reheat has an extended life cycle. An example of implementation is presented hereinafter along with the figures representing: Fig. 1, the thermo-mechanic diagram of the bullgear gas turbine with intercooler and reheat;
Fig. 2, the transmission diagram of the bullgear gas turbine with intercooler and reheat; Fig. 3, the thermodynamic cycle of the bullgear gas turbine with intercooler and reheat in enthalpy-entropy coordinates.
The bullgear gas turbine with intercooler and reheat, according to the invention, includes several turbo-compressor groups, each integrating the compressors (14,16,18,20,22), the shafts (8,9,10,11,12), the pinions (3,4,5,6,7) and the turbines (24,26,28,30,32). Before each compressor (16,18,20,22) there are placed the intercoolers (15,17,19,21) and before each turbine (24,26,28,30,32) there are the combustion chambers (23,25,27,29,31). The pinions (3,4,5,6,7) of each group interlocks at different speeds (nl,n2,n3,n4,n5) with the bullgear (1) having the speed (n) and delivering the power through the shaft (2) and the coupling (34) to the payload (33). The atmospheric air is admitted through the aspiration filter (13), passes the compressor (14) and is then delivered to the intercooler (15) and continues the layout through the compressors (16,18,20,22) with the intercoolers (17,19,21). The compressed air is sent into the combustion chamber (23), where the fuel (35) is injected, and then delivered to the turbine (24) following then the layout through the combustion chambers (25,27,29,31), with the fuel injections (36,37,38,39), with the appointed turbines (26,28,30,32) being then exhausted into the atmosphere as burned gases. The thermodynamic cycle accomplished by the gas turbine is represented in enthalpy-entropy coordinates and includes the compressions (101,103,105,107,109) with the intercooling (102,104,106,108), the combustion (110) and expansions (111,113,115,117,119) with the reheating (112,114,116,118). Starting from the atmospheric pressure pO, through subsequent compressions, there are reached the pressures pl,p3,p5,p7 and p9. The expansions start from the p9 pressure, there are reached the pressures p8,p6, p4,p2 and then the atmospheric pressure pO. The power obtained from each expansion is used for the appointed compression also resulting excedent energy due to fuel injections and combustions. The bullgear gas turbine with intercooling and reheat may integrate as many stages of compressions, intercooling, intermediary combustions and expansions, the efficiency increasing with the number of the stages.

Claims

1. Bullgear gas turbine with intercooler and reheat, consisting in a succession of compressors (14,16,18,20,22), combustion chambers (23,25,27,29,31) and turbines (24,26,28,30,32), defined by the fact that the succession of compressors (14,16,18,20,22) driven by appointed turbines (24,26,28,30,32) through appointed shafts (8,9,10,11,12) each with a pinion (3,4,5,6,7), each pinion having a different number of dents driving the bullgear (1) and therefore ensuring different speeds for each turbo-compressor group (14-24,16-25,18-27,20-29,22-31), the bullgear (1) driving in its turn, through a central shaft (2) and a coupling (34), a payload (33), and the first compressor (14) preceded by an aspiration filter (13), each of the following compressors (16,18,20,22) are preceded by a intercooler (15,17,19,21), each turbine (24,26,28,30,32) is preceded by a combustion chamber (23,25,27,29,31) with fuel injection and in the working cycle the air enters through the aspiration filter (13) into the first compressor (14) and is then cooled by the intercoolers (15,17,19,21) prior to entering each of the compressors (16,18,20,22), is then mixed with the fuel and burned in each of the combustion chambers (23,25,27,29,31) placed before each of the turbines (24,26,28,30,32) resulting the energy necessary to drive each turbine (24,26,28,30,32) distributed to each compressor (14,16,18,20,22) and the excedent is delivered through the shafts (8,9,10,11,12) and the pinions (3,4,5,6,7) to the bullgear (1) and to the payload (33).
2. Bullgear gas turbine with intercooler and reheat according to claim 1, defined by the fact that it may integrate as many stages of compressions, intercooling, intermediary combustions and expansions.
PCT/RO2010/000009 2009-07-13 2010-07-12 Bullgear gas turbine with intercooler and reheat WO2011112108A2 (en)

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ROA200900542 2009-07-13
RO200900542 2009-07-13

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WO2011112108A2 true WO2011112108A2 (en) 2011-09-15
WO2011112108A3 WO2011112108A3 (en) 2011-11-03

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2545538A (en) * 2015-10-27 2017-06-21 Rolls Royce Plc Gas turbine engine
CN110985337A (en) * 2019-12-02 2020-04-10 东方电气集团东方汽轮机有限公司 Integrated driving unit and operation method thereof

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4473754A (en) 1982-07-26 1984-09-25 Williams International Corporation Waste heat power generation system
EP0512568A1 (en) 1991-05-10 1992-11-11 Praxair Technology, Inc. System and method for integration of combustor-turbine units and compressors

Family Cites Families (5)

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US2073191A (en) * 1935-02-13 1937-03-09 Belluzzo Giuseppe Combustion turbine
GB574916A (en) * 1944-02-18 1946-01-25 Rene Strub Improvements in or relating to marine gas turbine plants
US2469238A (en) * 1947-08-28 1949-05-03 Westinghouse Electric Corp Gas turbine apparatus
FR1467556A (en) * 1966-02-07 1967-01-27 Caterpillar Tractor Co Gas turbine engine
US8336289B2 (en) * 2007-08-30 2012-12-25 United Technologies Corporation Gas turbine engine systems and related methods involving multiple gas turbine cores

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4473754A (en) 1982-07-26 1984-09-25 Williams International Corporation Waste heat power generation system
EP0512568A1 (en) 1991-05-10 1992-11-11 Praxair Technology, Inc. System and method for integration of combustor-turbine units and compressors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2545538A (en) * 2015-10-27 2017-06-21 Rolls Royce Plc Gas turbine engine
GB2545538B (en) * 2015-10-27 2018-03-14 Rolls Royce Plc A gas turbine engine having sequential combustion
CN110985337A (en) * 2019-12-02 2020-04-10 东方电气集团东方汽轮机有限公司 Integrated driving unit and operation method thereof

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