US3640646A - Air compressor system - Google Patents

Air compressor system Download PDF

Info

Publication number
US3640646A
US3640646A US22982A US3640646DA US3640646A US 3640646 A US3640646 A US 3640646A US 22982 A US22982 A US 22982A US 3640646D A US3640646D A US 3640646DA US 3640646 A US3640646 A US 3640646A
Authority
US
United States
Prior art keywords
compressor
air
line
gas turbine
compressed air
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
US22982A
Inventor
Hanns Hornschuch
William T Alderson
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.)
Ingersoll Rand Co
Original Assignee
Ingersoll Rand 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
Application filed by Ingersoll Rand Co filed Critical Ingersoll Rand Co
Application granted granted Critical
Publication of US3640646A publication Critical patent/US3640646A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C23/00—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids
    • F04C23/005—Combinations of two or more pumps, each being of rotary-piston or oscillating-piston type, specially adapted for elastic fluids; Pumping installations specially adapted for elastic fluids; Multi-stage pumps specially adapted for elastic fluids of dissimilar working principle

Definitions

  • the principal object of this invention is to provide a novel portable air compressor driven by a gas turbine.
  • an air compressor system including a first compressor driven by a gas turbine with a part of the air handled by the air compressor going to the gas turbine as combustion air.
  • the remainder of the air from the first compressor is boosted by a second compressor of positive displacement design and driven by the gas turbine.
  • the compressed air from the second compressor flows to a line for use as compressed air. Due to the use of the positive displacement compressor as the second compressor, the compressed air delivered from the system can be varied over a wide range of pressures, say 100 to 300 p.s.i.g.
  • FIGURE in the drawing is a schematic diagram of the novel gas turbine air compressor of this invention.
  • the single figure in the drawing schematically discloses a drive shaft 1 driven by a two-stage turbine wheel 2 and driving a two-stage centrifugal compressor 3 and a positive displacement rotary compressor 4 of the screw type. Air is sucked into the inlet 5 of the two-stage centrifugal compressor 3, is compressed in the first stage, passes through an intercooler 7 and then through the second stage. The air exits from the second stage into an outlet line 8 which feeds it to a dividing valve 9.
  • the dividing valve 9 divides the air into two parts, one part for use as combustion air in the gas turbine 2 and the other part for use as compressed air.
  • the combustion air exits from the valve 9 through a line 10 to an air heater 11 mounted in the exhaust line of the gas turbine 2 for recapturing some of the heat in the turbine exhaust gases and using it to heat the combustion air.
  • the combustion air flows from the air heater 11 though a line 12 to the combustion chamber 14.
  • the combustion air mixes with fuel in the combustion chamber with the resulting mixture being ignited and combusted before entering the turbine 2 where it expends a part of its energy by driving the turbine 2.
  • the other portion of the air in the dividing valve 9 which will be used as compressed air flows through a line 15 to an after cooler 16 where it is cooled before entering a line 17 feeding it to the positive displacement screw compressor 4.
  • This air is boosted in pressure in the compressor 4 and is then fed through the line 19 to a compressed air receiver 20.
  • the exit port of the receiver is connected to an air line 21 through a valve 22.
  • An air compressor system comprising:
  • a single gas turbine drivingly coupled to said first and second compressors, and having a combustion chamber; single air inlet means for admitting air to said first and second compressors and to said gas turbine;
  • heat exchange means interposed in said first line and in gas flow communication with the discharge port of said gas turbine;
  • an intercooler located between said two stages of said first compressor.
  • the air compressor system of claim 1 including:
  • an intercooler located in said second line for cooling compressed air flowing through said second line.
  • sad second compressor is a positive displacement type of compressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A gas turbine driven air compressor system including a first compressor feeding a portion of its compressed air to the turbine for combustion purposes and a second positive displacement compressor receiving the remaining compressed air from the first compressor and boosting its pressure for use as compressed air.

Description

O Unlted States Patent 1 51 3,640,646 Hornschuch et al. 1 Feb. 8, 1972 [54] AIR COMPRESSOR SYSTEM 1,927,799 9/1933 Mann ..417/203 [72] inventors: Hanns Hornschuch Eamon, Pa; William 2,741,422 4/1956 Kockritz et a1. .417/20 Alder-819 Bmkslde FOREIGN PATENTS 0R APPLICATIONS [731 Assign: lngemll'kand 912,054 7/1946 France 417/3s1 [22] Filed: Mar. 26, 1970 Primary Examiner-Robert M. Walker 1 1 p N01 22,982 Attorney-Frank S.Troid1, Bernard J. Murphy and David w.
Tibbott [52] U.S.Cl ..417/203,417/243,417/381 1 5 1 1 1111. C1 ..F04b 23/14, F04b 23/00, F04b 17/00 A RA [58] held of Search 12 A gas turbine driven air compressor system including a first I compressor feeding a portion of its compressed air to the turl56 References Cited bme for combustion purposes and a second POS1UV displacement compressor receiving the remaining compressed air UNITED STATES PATENTS from the first compressor and boosting its pressure for use as compressed air. 2,811,362 10/1957 Hodge et al ..417/409 X 2,628,015 2/1953 Neugebauer et al. ..417/243 X 3 Claims, 1 Drawing Figure FUEL Pmmsorw a ma 3.610.648
INVENTORS HA IVA .5 HOR/VSCHUGH W/L 1. MM 7: ALDERSO/V AGENT AIR COMPRFSSOR SYSTEM BACKGROUND OF INVENTION The present invention relates to an air compressor system utilizing a gas turbine as a prime mover or driver.
Conventional portable air compressors are driven by reciprocating internal combustion engines. In the larger portable compressors, say 1,000 c.f.m. or higher, the use of reciprocating engines makes the portable compressor relatively large and heavy. As a result, it is impractical today to build engine-driven portable compressors having a capacity of more than 1,200 c.f.m.
SUMMARY OF INVENTION The principal object of this invention is to provide a novel portable air compressor driven by a gas turbine.
Other important objects of this invention are; to provide a more efficient air compressor unit driven by a gas turbine; to provide an air compressor driven by a gas turbine in which part of the compressed air is used in the gas turbine; and to provide a gas turbine driven air compressor having a readily variable discharge pressure ranging from about 100 to 30 p.s.i.g.
In general, the foregoing objects are attained in an air compressor system including a first compressor driven by a gas turbine with a part of the air handled by the air compressor going to the gas turbine as combustion air. The remainder of the air from the first compressor is boosted by a second compressor of positive displacement design and driven by the gas turbine. The compressed air from the second compressor flows to a line for use as compressed air. Due to the use of the positive displacement compressor as the second compressor, the compressed air delivered from the system can be varied over a wide range of pressures, say 100 to 300 p.s.i.g.
BRIEF DESCRIPTION OF DRAWING The single FIGURE in the drawing is a schematic diagram of the novel gas turbine air compressor of this invention.
DESCRIPTION OF SPECIFIC EMBODIMENT The single figure in the drawing schematically discloses a drive shaft 1 driven by a two-stage turbine wheel 2 and driving a two-stage centrifugal compressor 3 and a positive displacement rotary compressor 4 of the screw type. Air is sucked into the inlet 5 of the two-stage centrifugal compressor 3, is compressed in the first stage, passes through an intercooler 7 and then through the second stage. The air exits from the second stage into an outlet line 8 which feeds it to a dividing valve 9. The dividing valve 9 divides the air into two parts, one part for use as combustion air in the gas turbine 2 and the other part for use as compressed air.
The combustion air exits from the valve 9 through a line 10 to an air heater 11 mounted in the exhaust line of the gas turbine 2 for recapturing some of the heat in the turbine exhaust gases and using it to heat the combustion air. The combustion air flows from the air heater 11 though a line 12 to the combustion chamber 14. The combustion air mixes with fuel in the combustion chamber with the resulting mixture being ignited and combusted before entering the turbine 2 where it expends a part of its energy by driving the turbine 2.
The other portion of the air in the dividing valve 9 which will be used as compressed air flows through a line 15 to an after cooler 16 where it is cooled before entering a line 17 feeding it to the positive displacement screw compressor 4. This air is boosted in pressure in the compressor 4 and is then fed through the line 19 to a compressed air receiver 20. The exit port of the receiver is connected to an air line 21 through a valve 22.
While a single embodiment of the invention is illustrated and described, it should be understood that this invention is not limited merely to the particular structure described in the specification and shown in the drawin but may include other embodiments and modifications utrrzing the concept an teachings of the invention.
I claim:
1. An air compressor system, comprising:
a first compressor having two stages for compression;
a second compressor;
a single gas turbine, drivingly coupled to said first and second compressors, and having a combustion chamber; single air inlet means for admitting air to said first and second compressors and to said gas turbine;
a first line interconnecting the discharge port of said first compressor to said combustion chamber of said gas turbine;
heat exchange means, interposed in said first line and in gas flow communication with the discharge port of said gas turbine;
a second line interconnecting said first line to the inlet port of said second compressor whereby a portion of the compressed air discharged by said first compressor is delivered to said second compressor;
a third line receiving compressed air from said second compressor for use in operating compressed air equipment; and
an intercooler located between said two stages of said first compressor.
2. The air compressor system of claim 1 including:
an intercooler located in said second line for cooling compressed air flowing through said second line.
3. The air compressor system of claim I wherein:
sad second compressor is a positive displacement type of compressor.

Claims (3)

1. An air compressor system, comprising: a first compressor having two stages for compression; a second compressor; a single gas turbine, drivingly coupled to said first and second compressors, and having a combustion chamber; single air inlet means for admitting air to said first and second compressors and to said gas turbine; a first line interconnecting the discharge port of said first compressor to said combustion chamber of said gas turbine; heat exchange means, interposed in said first line and in gas flow communication with the discharge port of said gas turbine; a second line interconnecting said first line to the inlet port of said second compressor whereby a portion of the compressed air discharged by said first compressor is delivered to said second compressor; a third line receiving compressed air from said second compressor for use in operating compressed air equipment; and an intercooler located between said two stages of said first compressor.
2. The air compressor system of claim 1 including: an intercooler located in said second line for cooling compressed air flowing through said second line.
3. The air compressor system of claim 1 wherein: said second compressor is a positive displacement type of compressor.
US22982A 1970-03-26 1970-03-26 Air compressor system Expired - Lifetime US3640646A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US2298270A 1970-03-26 1970-03-26

Publications (1)

Publication Number Publication Date
US3640646A true US3640646A (en) 1972-02-08

Family

ID=21812448

Family Applications (1)

Application Number Title Priority Date Filing Date
US22982A Expired - Lifetime US3640646A (en) 1970-03-26 1970-03-26 Air compressor system

Country Status (1)

Country Link
US (1) US3640646A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4254758A (en) * 1979-08-17 1981-03-10 Banks George W Vortex heat reclaiming system
US6402482B1 (en) * 1998-03-20 2002-06-11 Heon Seok Lee Small turbo compressor
US20040184927A1 (en) * 2001-07-30 2004-09-23 Kolodziej Robert M. Air cooled packaged multi-stage centrifugal compressor system
US20070217939A1 (en) * 2006-03-20 2007-09-20 Kazuho Sato Gas-compression module for a fuel cell
US20090257902A1 (en) * 2006-06-01 2009-10-15 Philippe Alphonse Louis Ernens Compressor device
CN103352831A (en) * 2012-07-09 2013-10-16 摩尔动力(北京)技术股份有限公司 Hybrid gas compressing system and thermo-power system applying same
CN104832287A (en) * 2014-03-25 2015-08-12 摩尔动力(北京)技术股份有限公司 Speed-volume turbine engine
DE102014107126A1 (en) 2014-05-20 2015-11-26 Harald Wenzel Multi-stage compressor system for generating a compressed gas
WO2017180554A1 (en) * 2016-04-11 2017-10-19 Atlas Copco Comptec, Llc Integrally geared compressor having a combination of centrifugal and positive displacement compression stages

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1927799A (en) * 1932-03-07 1933-09-19 Goulds Pumps Rotary pump
FR912054A (en) * 1944-03-18 1946-07-30 Sulzer Ag Installation of gas turbines with motor agent circuit
US2628015A (en) * 1949-11-09 1953-02-10 Franz J Neugebauer Engine-driven air compressor
US2741422A (en) * 1953-10-09 1956-04-10 Brown Boveri & Compagnie Ag Gas turbine plant
US2811302A (en) * 1954-02-24 1957-10-29 Power Jets Res & Dev Ltd Gas turbine plant and control arrangements therefor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1927799A (en) * 1932-03-07 1933-09-19 Goulds Pumps Rotary pump
FR912054A (en) * 1944-03-18 1946-07-30 Sulzer Ag Installation of gas turbines with motor agent circuit
US2628015A (en) * 1949-11-09 1953-02-10 Franz J Neugebauer Engine-driven air compressor
US2741422A (en) * 1953-10-09 1956-04-10 Brown Boveri & Compagnie Ag Gas turbine plant
US2811302A (en) * 1954-02-24 1957-10-29 Power Jets Res & Dev Ltd Gas turbine plant and control arrangements therefor

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4254758A (en) * 1979-08-17 1981-03-10 Banks George W Vortex heat reclaiming system
US6402482B1 (en) * 1998-03-20 2002-06-11 Heon Seok Lee Small turbo compressor
US7832992B2 (en) * 2001-07-30 2010-11-16 Cameron International Corporation Air cooled packaged multi-stage centrifugal compressor system
US20040184927A1 (en) * 2001-07-30 2004-09-23 Kolodziej Robert M. Air cooled packaged multi-stage centrifugal compressor system
US20080273991A1 (en) * 2001-07-30 2008-11-06 Cameron International Corporation Air cooled packaged multi-stage centrifugal compressor method
US7819634B2 (en) 2001-07-30 2010-10-26 Cameron International Corporation Air cooled packaged multi-stage centrifugal compressor method
US20070217939A1 (en) * 2006-03-20 2007-09-20 Kazuho Sato Gas-compression module for a fuel cell
US8197227B2 (en) * 2006-06-01 2012-06-12 Atlas Copco Airpower, Naamloze Vennootschap Multi-stage compressor system
US20090257902A1 (en) * 2006-06-01 2009-10-15 Philippe Alphonse Louis Ernens Compressor device
CN103352831A (en) * 2012-07-09 2013-10-16 摩尔动力(北京)技术股份有限公司 Hybrid gas compressing system and thermo-power system applying same
CN104832287A (en) * 2014-03-25 2015-08-12 摩尔动力(北京)技术股份有限公司 Speed-volume turbine engine
CN104832287B (en) * 2014-03-25 2016-10-05 摩尔动力(北京)技术股份有限公司 Speed holds turbine engine
DE102014107126A1 (en) 2014-05-20 2015-11-26 Harald Wenzel Multi-stage compressor system for generating a compressed gas
WO2015176710A1 (en) 2014-05-20 2015-11-26 Harald Wenzel Multistage compressor system with hydrodynamic fluid coupling
DE212015000133U1 (en) 2014-05-20 2017-05-04 Harald Wenzel Multi-stage compressor unit for generating a compressed gas
WO2017180554A1 (en) * 2016-04-11 2017-10-19 Atlas Copco Comptec, Llc Integrally geared compressor having a combination of centrifugal and positive displacement compression stages
CN107288857A (en) * 2016-04-11 2017-10-24 阿特拉斯科普柯康珀泰克有限责任公司 The integrated form gear drive compressor combined with centrifugal and positive displacement compression stage
US10502217B2 (en) 2016-04-11 2019-12-10 Atlas Copco Comptec, Llc Integrally geared compressor having a combination of centrifugal and positive displacement compression stages
US11686316B2 (en) 2016-04-11 2023-06-27 Atlas Copco Comptec, Llc Integrally geared compressor having a combination of centrifugal and positive displacement compression stages

Similar Documents

Publication Publication Date Title
US3143103A (en) Multi-stage supercharger with separate outlet for cooling air
US3204859A (en) Gas compressor system
EP2011962B1 (en) Compound cycle rotary engine
US4021215A (en) Dual combined cycle air-conditioning system
US6050082A (en) Intercooled gas turbine engine with integral air bottoming cycle
US2375006A (en) Supercharged combustion engine arrangement
US4344289A (en) Two-stage supercharging apparatus
US2849173A (en) Compressor system
US20220307408A1 (en) Structural arrangement in a low-temperature turbocompressor for an internal combustion engine
US2966776A (en) Pneumatic power transmission system
US3640646A (en) Air compressor system
US6526751B1 (en) Integrated turbocharger ejector intercooler with partial isothermal compression
US6966183B2 (en) Supercharged internal combustion engine
JPH1193681A (en) Hydrogen-fueled engine
US3102381A (en) Engine inlet-exhaust bypass means for exhaust driven superchargers
US2703560A (en) Supercharging system
US2877622A (en) Heat engines
CN112727593B (en) Air cooling chamber assembly and internal combustion engine with air cooling chamber assembly
US2766744A (en) Turbo-cooling means for non-supercharged dual-fuel two-cycle internal combustion engines
GB1573193A (en) Reciprocating piston internal combustion engine and turbocharger assembly
US3727399A (en) Rotary-piston diesel engine superchargers
US6726457B2 (en) Compressor with supercharged inlet
US2970433A (en) Compound gas turbine plants
US3796047A (en) Engine supercharging air cooling system
US4610141A (en) Compound engine with plural stage intercooled exhaust pump