WO1990001624A1 - Moteur de turbine avec refroidisseur intermediaire a haute pression - Google Patents

Moteur de turbine avec refroidisseur intermediaire a haute pression Download PDF

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Publication number
WO1990001624A1
WO1990001624A1 PCT/US1989/003227 US8903227W WO9001624A1 WO 1990001624 A1 WO1990001624 A1 WO 1990001624A1 US 8903227 W US8903227 W US 8903227W WO 9001624 A1 WO9001624 A1 WO 9001624A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
spools
low
pressure
high pressure
Prior art date
Application number
PCT/US1989/003227
Other languages
English (en)
Inventor
Colin Rogers
Robert J. Geiser
Original Assignee
Sundstrand Corporation
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 Sundstrand Corporation filed Critical Sundstrand Corporation
Publication of WO1990001624A1 publication Critical patent/WO1990001624A1/fr

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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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • 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

Definitions

  • This invention relates to turbine engines, and more particularly, to a compound, turbine engine operating under high pressure with intercooling between compression stages.
  • Ford Motor Company has developed a gas turbine engine known as the 704/705 with a somewhat similar cycle. In this engine, the intercooler was air cooled, resulting in higher losses and reduced intercooling efficiency. Both of these developments were too complex for the then current state of the art.
  • the present invention is directed to overcoming one or more of the above problems.
  • An exemplary embodiment of the invention achieves the foregoing object in a compound gas turbine engine including at least three independently rotatable spools.
  • a first of the spools includes a low pressure compressor and a low pressure turbine.
  • a second of the spools includes an intermediate pressure compressor and an intermediate pres ⁇ sure turbine.
  • Still a third of the spools includes a high pressure compressor and a high pressure turbine.
  • At least two interstage intercoolers are provided and compressed air ducting connects one of the intercoolers between the low and intermediate pressure compressors and further connects the other of the intercoolers between the intermediate and high pressure compressors.
  • At least one combustor for burning fuel to produce gases of combustion and the same is con ⁇ nected between the high pressure compressor and the high pressure turbine.
  • the combustor receives compressed air from the high pressure compressor and burns fuel and directs the resulting gases of combustion to the high pressure turbine.
  • Combustion gas ducting connects the high and the intermediate pressure turbines and also connects the inter ⁇ mediate and low pressure turbines. Power take-off means are provided for the engine.
  • each of the low, intermediate and high pressure compressors is a radial flow compressor.
  • the low pressure spool includes a shaft and each of the interstage intercoolers includes a cooling air inlet and a cooling air outlet.
  • liquid cooling means could be used instead of air.
  • the power take-off is in the form of a separate free power turbine connected to receive combustion gas from the low pressure turbine.
  • a reheater may be selectively opera ⁇ ted to heat combustion gas passing from the low pressure turbine to the free power turbine and a fan is mounted on the shaft of the first spool to be driven by the low power turbine. Cooling air ducting connects the fan and the cooling air inlets of the intercoolers.
  • the spools are generally coplanar and disposed and spaced, side by side, parallel relation.
  • An air inlet is provided in alignment with the low pressure spool on the compressor side thereof and the fan is disposed in such inlet.
  • the compressed air ducting extends generally transverse to the spools on the compressor sides thereof and the cooling air ducting is in heat exchange relation with the compressed air ducting along the length thereof to define the two intercoolers.
  • the spools are disposed and spaced, side by side, triangular, parallel relation and there is provided an air inlet with the fan disposed in the inlet as before.
  • the cooling air ducting comprises at least two generally radially disposed ducts terminating at a cooling air inlet of a respective one of the intercoolers.
  • the low and intermediate pressure spools in the free power turbine are coaxial.
  • the high pressure spool is disposed to one side of the low and intermediate pressure spools and rearwardly thereof.
  • the intercoolers are located forwardly of the high pressure spool and generally in axial alignment therewith and to one side of the low and inter ⁇ mediate pressure spools.
  • the low and intermediate turbines in the free power turbines * are axial flow turbines.
  • Fig. 1 is a schematic flow diagram illustrating the organization of the various components of all embodiments of the invention with respect to each other;
  • Fig. 2 is a sectional view of one embodiment of a gas turbine engine made according to the invention
  • Fig. 3 is a front elevation of the embodiment of Fig. 2;
  • Fig. 4 is a side elevation of the embodiment of Fig. 2 with certain parts shown in section for clarity;
  • Fig. 5 is a sectional view of another embodiment of the invention.
  • Fig. 6 is a front elevation of the embodiment of Fig. 5;
  • Fig. 7 is a sectional view of a highly preferred embodiment of the invention.
  • Fig. 8 is a rear elevation of the embodiment of Fig. 7.
  • FIG. 1 A schematic flow diagram of a compound gas turbine engine made according to the invention is illustrated in Fig. 1.
  • the invention includes four independently rotatable spools generally designated 10, 12, 14, and 16.
  • the spool 10 is a low pressure spool and includes a radial flow compressor 18 and a turbine wheel 20.
  • the spool 10 also includes a shaft shown schematically at 22 which extends intc an air inlet 24 for the engine. Within the inlet 24, a fan 26 is mounted on the shaft 22. Cooling air ducting 28 extends from the inlet 24 at a location therein just down ⁇ stream of the fan 26 but upstream of the compressor 18 to first and second intercoolers generally designated 30 and 32.
  • the spool 12 is an intermediate pressure spool and includes a radial flow compressor 34 and interconnected turbine 36.
  • Ducting 38 which includes a passage through the intercooler 30, interconnects the outlet of the " com ⁇ pressor 18 and the inlet of the compressor 34.
  • the spool 14 is a high pressure spool and includes a radial flow compressor 40 and a turbine 42.
  • Ducting 44 interconnects the outlet of the compressor 34 and the inlet of the compressor 40 via a path through the intercooler 32.
  • cooling air taken from the inlet 24 is utilized in the intercoolers 30 and 32 to provide interstage cooling of combustion air, also taken from the inlet 24, after it has been initially compressed by the low pressure compressor 18 and again after it has been further compressed by the intermediate pressure compressor 34.
  • a separate fan or pump driven by suitable means could be used to provide air or liquid coolant, respectively, to the intercoolers 30 and 32.
  • the outlet of the high pressure compressor 40 is connected to a conventional combustor 46.
  • the combustor 46 receives compressed air from the compressor 40 as well as fuel from a source not shown, burns the same and provides combustion gas to the turbine 42 so that the latter will rotate and drive the compressor 40.
  • Gases of combustion exiting the turbine 42 are conveyed via ducting 48 to the inlet of the turbine 36 to drive the same and thus drive the compressor 34.
  • Additional ducting 50 conducts gases of combustion from the turbine 36 to the low pressure turbine 20 to drive the same. This in turn results in rotation of the low pressure compressor 18 as well as the fan 26.
  • the fourth spool 16 consists of a free power turbine 52 which may be connected through suitable gearing 54 to an output shaft 56.
  • Ducting 58 including a reheat combustor 60, interconnects the low pressure turbine 20 and the free power turbine 52.
  • the reheat combustor 60 may or may not be used as desired and where a given application permits the same to be selectively used, the free power turbine 52 is provided with a variable power turbine nozzle schematically illustrated at 62.
  • the interstage intercoolers increase the density of the air by reducing the temperature thereof, thereby enabling the attainment of relatively high pressure ratios as is desired.
  • each of the spools 10, 12, 14 and 16 is independently rotatable on its associated rotational axis 100, 102, 104 and 106.
  • each of the turbines 20, 36, 42 and 52 in this embodiment are radial flow turbines.
  • the combustor 46 is an annular combustor disposed about the axis 104 of the spool 14.
  • the power take-off shaft 56 is displaced from the axis of rotation 106 of the free power turbine 52 which, if desired, can be coaxial with the axis 102. It will be observed from Fig. 3 that the various axes are parallel such that the spools are in side by side relation and generally coplanar.
  • a volute 108 surrounds the low pressure compressor 18.
  • the volute 108 opens as at 110 into the interior of a plenum 112 which is in fluid communication with the inlet 114 -to the intermediate pressure compressor 34.
  • a partition 116 (Fig. 3) may divide the plenum 112 into two sections such that a volute 118 surrounding the inter ⁇ mediate stage compressor 34 may discharge via an opening 120 into the lowermost section which in turn is in fluid com ⁇ munication with the inlet 122 to the high pressure compres ⁇ sor 40.
  • the plenum 112 thus forms ducting for the compressed air, which ducting extends generally transverse to the various axes of rotation and across the front of the engine.
  • suitable means shown schematically at 124 for dividing the same into two separate flow paths in heat exchange relation with one another. This is, of course, to define the intercoolers 30 and 32 and the precise internal configuration is well within the skill of the art.
  • the partition 124 in addition to defin ⁇ ing the intercoolers 30 and 32, defines a cooling air duct opening as at 126 to the inlet 24 downstream of the fan 26 and upstream of the low pressure compressor 18. An outlet for the cooling air is shown at 128.
  • Ducting 130 extends from the discharge side of the high pressure turbine 42 to a nozzle 132 surrounding the turbine 36 of the intermediate pressure spool 12. Additional ducting 134 extends from the outlet side of the intermediate pressure turbine 36 to a nozzle 136 surrounding the low pressure turbine 20. The ducting 58 then extends " to a variable nozzle 140 associated with free power turbine 16.
  • the embodiment of Figs. 2-4, inclusive is advantageous in that it allows the use of modular spools and avoids mechani ⁇ cal complexity that would be associated with concentric shafting. This embodiment is ideally suited for appli ⁇ cations where engine volume is not of particular concern such as ground power or marine applications.
  • FIGs. 5 and 6 Another embodiment of the invention is illustrated in Figs. 5 and 6. * This embodiment of the invention is very much like that illustrated in Figs. 2-4 but has the added advantage of reduced frontal area. It has a disadvantage of more complicated ducting.
  • the spools 10, 12, 14 and 16 respectively rotate on axes 200, 202, 204 and 206.
  • the inlet 24 is generally coaxial with the axis of rotation of the low pressure spool 10, here the axis 200.
  • the intercoolers 30 and 32 have inlets 208 and outlets for the compressed air which is received through ducting 212 serving the function of the ducting 38 and 44.
  • the intercoolers 30 and 32 have cooling air inlets 214 which open radially inwardly and which are connected by ducts that extend radially from the inlet 24 and open thereto at a location intermediate the fan 26 and the low pressure spool 10. Cooling air outlets (not shown) are naturally provided.
  • Figs. 7 and 8 A highly preferred embodiment is illustrated in Figs. 7 and 8. Though mechanically somewhat more complex than either of the two embodiments heretofore described, it offers the advantage of substantially reduced frontal area and retains relatively simple ducting.
  • the spools 10, 12 and 16 are rotatable about a single axis 300.
  • the spool 16 is located to the rear of the spools 10 and 12 and the latter include concentric shafts 302 and 304.
  • the shaft 302 drives the fan 26 and thus corresponds to the shaft 22. That is to say, the shaft 302 is associated with the low pressure spool 10.
  • the shaft 304 is a hollow shaft receiving the shaft 302 and is associated with the inter ⁇ mediate pressure spool 12.
  • the low pressure turbine 20, the intermediate pressure turbine 36, and the free power turbine 52 are all axial * flow turbines.
  • the compressor 18, 34 and 40 are all radial flow compressors while the high pressure turbine 42 is a radial inflow turbine.
  • the high pressure spool 14 is disposed to one side of the spools 10, 12 and 16 and to the rear of the spools 10 and 12.
  • the intercoolers 30 and 32 are generally aligned with the high pressure spool 14, that is, its axis of rotation 306 if projected would extend through the intercoolers 30 and 32.
  • the intercoolers 30 and 32 are nominally aligned with the spools 10 and 12 from front to rear and displaced to the same side of the axis 300 as is the high pressure spool 14.
  • the intercoolers 30 and 32 may have outlets 308 opening to opposite sides of the axis 306 as illustrated in Fig. 8 and ducting 310 serving the purpose of the ducting 28 extends from a location in the inlet 24 between the fan 36 and the low pressure compressor 18 to inlets (not shown) for the intercoolers 30 and 32.
  • a Brayton cycle gas turbine engine made according to the invention is capable of operating at high pressure ratios and may be configured in various ways depending upon the application to which it is to be put.
  • a Brayton cycle gas turbine engine capable of thermal efficiencies approach ⁇ ing those obtainable with diesel engines is provided.

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

Abstract

On obtient des taux de haute pression dans un moteur de turbine à gaz à cycle de Brayton en utilisant une bobine basse pression (10), une bobine à pression intermédiaire (12) et une bobine haute pression (14). Des refroidisseurs intermédiaires (30 et 32) sont placés entre les étages définis par les bobines (10, 12 et 14) dans le but de densifier l'air comprimé par un compresseur basse pression (18) et un compresseur intermédiaire (34) associé aux bobines (10 et 12) respectivement.
PCT/US1989/003227 1988-08-09 1989-07-26 Moteur de turbine avec refroidisseur intermediaire a haute pression WO1990001624A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US23025788A 1988-08-09 1988-08-09
US230,257 1988-08-09

Publications (1)

Publication Number Publication Date
WO1990001624A1 true WO1990001624A1 (fr) 1990-02-22

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PCT/US1989/003227 WO1990001624A1 (fr) 1988-08-09 1989-07-26 Moteur de turbine avec refroidisseur intermediaire a haute pression

Country Status (3)

Country Link
EP (1) EP0381755A4 (fr)
JP (1) JPH03500797A (fr)
WO (1) WO1990001624A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2288640A (en) * 1994-04-16 1995-10-25 Rolls Royce Plc Gas turbine engine combustion arrangement
WO2013141943A1 (fr) * 2011-12-31 2013-09-26 Rolls-Royce Corporation Chambre de combustion de turbine à gaz
US10851704B2 (en) 2018-12-14 2020-12-01 Transportation Ip Holdings, Llc Systems and methods for increasing power output in a waste heat driven air brayton cycle turbocharger system
US11041437B2 (en) 2018-12-14 2021-06-22 Transportation Ip Holdings, Llc Systems and methods for increasing power output in a waste heat driven air Brayton cycle turbocharger system

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2312605A (en) * 1938-12-24 1943-03-02 Sulzer Ag Gas turbine plant
US2584232A (en) * 1946-09-04 1952-02-05 Rateau Soc Gas turbine power plant, including means to treat combustion products between successive stages of expansion
US3842597A (en) * 1973-03-16 1974-10-22 Gen Electric Gas turbine engine with means for reducing the formation and emission of nitrogen oxides
US4244191A (en) * 1978-01-03 1981-01-13 Thomassen Holland B.V. Gas turbine plant
US4254618A (en) * 1977-08-18 1981-03-10 General Electric Company Cooling air cooler for a gas turbofan engine
JPS59120720A (ja) * 1982-12-27 1984-07-12 Osaka Gas Co Ltd ガスタ−ビン装置
US4509324A (en) * 1983-05-09 1985-04-09 Urbach Herman B Direct open loop Rankine engine system and method of operating same
US4592204A (en) * 1978-10-26 1986-06-03 Rice Ivan G Compression intercooled high cycle pressure ratio gas generator for combined cycles
US4645415A (en) * 1983-12-23 1987-02-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2312605A (en) * 1938-12-24 1943-03-02 Sulzer Ag Gas turbine plant
US2584232A (en) * 1946-09-04 1952-02-05 Rateau Soc Gas turbine power plant, including means to treat combustion products between successive stages of expansion
US3842597A (en) * 1973-03-16 1974-10-22 Gen Electric Gas turbine engine with means for reducing the formation and emission of nitrogen oxides
US4254618A (en) * 1977-08-18 1981-03-10 General Electric Company Cooling air cooler for a gas turbofan engine
US4244191A (en) * 1978-01-03 1981-01-13 Thomassen Holland B.V. Gas turbine plant
US4592204A (en) * 1978-10-26 1986-06-03 Rice Ivan G Compression intercooled high cycle pressure ratio gas generator for combined cycles
JPS59120720A (ja) * 1982-12-27 1984-07-12 Osaka Gas Co Ltd ガスタ−ビン装置
US4509324A (en) * 1983-05-09 1985-04-09 Urbach Herman B Direct open loop Rankine engine system and method of operating same
US4645415A (en) * 1983-12-23 1987-02-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP0381755A4 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2288640A (en) * 1994-04-16 1995-10-25 Rolls Royce Plc Gas turbine engine combustion arrangement
US5743081A (en) * 1994-04-16 1998-04-28 Rolls-Royce Plc Gas turbine engine
GB2288640B (en) * 1994-04-16 1998-08-12 Rolls Royce Plc A gas turbine engine
WO2013141943A1 (fr) * 2011-12-31 2013-09-26 Rolls-Royce Corporation Chambre de combustion de turbine à gaz
US10295191B2 (en) 2011-12-31 2019-05-21 Rolls-Royce Corporation Gas turbine engine and annular combustor with swirler
US10851704B2 (en) 2018-12-14 2020-12-01 Transportation Ip Holdings, Llc Systems and methods for increasing power output in a waste heat driven air brayton cycle turbocharger system
US11041437B2 (en) 2018-12-14 2021-06-22 Transportation Ip Holdings, Llc Systems and methods for increasing power output in a waste heat driven air Brayton cycle turbocharger system

Also Published As

Publication number Publication date
JPH03500797A (ja) 1991-02-21
EP0381755A4 (en) 1990-12-27
EP0381755A1 (fr) 1990-08-16

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