EP2019924A2 - Technique de contrôle d'écoulement pour guider un écoulement en vrac vectoriel quittant une aube - Google Patents

Technique de contrôle d'écoulement pour guider un écoulement en vrac vectoriel quittant une aube

Info

Publication number
EP2019924A2
EP2019924A2 EP07868284A EP07868284A EP2019924A2 EP 2019924 A2 EP2019924 A2 EP 2019924A2 EP 07868284 A EP07868284 A EP 07868284A EP 07868284 A EP07868284 A EP 07868284A EP 2019924 A2 EP2019924 A2 EP 2019924A2
Authority
EP
European Patent Office
Prior art keywords
wall
trailing edge
vane
assembly
annular casing
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.)
Withdrawn
Application number
EP07868284A
Other languages
German (de)
English (en)
Inventor
David R. Williams
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.)
Acharya Mukund
Honeywell International Inc
Original Assignee
Acharya Mukund
Honeywell International Inc
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 Acharya Mukund, Honeywell International Inc filed Critical Acharya Mukund
Publication of EP2019924A2 publication Critical patent/EP2019924A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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 present invention relates to a gas turbine engine and, more particularly, to vanes for use in a fan section or a compressor section of the engine.
  • Turbofan gas turbine engines typically include five major sections, for example, a fan section, a compressor section, a combustor section, a turbine section, and an exhaust section.
  • the fan section is positioned at the front, or "inlet” section of the engine, and includes a fan that induces air from the surrounding environment into the engine, and accelerates a fraction of this air toward the compressor section. The remaining fraction of air induced into the fan section is accelerated into and through a bypass plenum, and out the exhaust section.
  • the compressor section which may include one or more compressors, raises the pressure of the air it receives from the fan section to a relatively high level.
  • the compressed air then enters the combustor section, where a ring of fuel nozzles injects a steady stream of fuel.
  • the injected fuel is ignited by a burner, significantly increasing the energy of the resulting hot, compressed gases, and the gases then flow into and through the turbine section to cause rotationally mounted turbine blades to rotate and generate energy.
  • the gases exiting the turbine section are exhausted from the engine via the exhaust section, and the energy remaining in this exhaust stream aids the thrust generated by the air flowing through the bypass plenum.
  • a guide vane assembly is typically disposed therein.
  • the guide vane assembly includes variable geometry guide vanes that typically extend radially inward from the annular casing towards a hub.
  • the guide vanes are coupled to a plurality of actuators via unison rings, linkages, and bell- cranks, that, when moved, changes the positioning of the guide vanes to thereby control the direction and amount of airflow into downstream sections of the engine.
  • the above-described assembly adequately controls airflow, it suffers from certain drawbacks.
  • the guide vanes are fixed in a single position during aircraft operation or scheduled to be set at pre-determined positions based on engine speed; thus, they may not adequately respond to a rapid airflow change in the event a distortion is present in the compressor.
  • the engine may not operate as efficiently with the fixed guide vanes.
  • the guide vane assembly includes many components which may undesirably add weight and/or cost to an aircraft.
  • the present invention provides a guide vane assembly.
  • the inlet guide vane assembly includes an annular casing, and a plurality of vanes.
  • the plurality of vanes is coupled to and extends radially inwardly from the annular casing.
  • Each vane includes a first wall, a second wall, a leading edge, a first wall trailing edge, and a second wall trailing edge.
  • the first and second walls are coupled at the leading edge and spaced apart to define a plenum therebetween.
  • the first and second wall trailing edges are spaced apart to define a gap therebetween.
  • the first wall trailing edge includes a lip extending therefrom toward the second wall, and the second wall trailing edge includes a bulb section extending along at least a portion of a length thereof.
  • the second wall trailing edge is disposed at least partially inside the lip, wherein a substantial entirety of the vane between an outer surface of the second wall and an outer surface of the bulb portion is rounded.
  • the guide vane assembly includes an annular casing and a plurality of vanes.
  • the annular casing includes a manifold and a plurality of openings in communication with the manifold.
  • the plurality of vanes is coupled to and extends radially inwardly from the casing, and each vane includes a first wall, a second wall, a leading edge, a first wall trailing edge, a second wall trailing edge, and a stem.
  • the first and second walls are coupled at the leading edge and spaced apart to define a plenum therebetween.
  • the first and second wall trailing edges are spaced apart to define a gap therebetween.
  • the first wall trailing edge includes a lip extending therefrom toward the second wall, and the second wall trailing edge includes a bulb section extending along at least a portion of a length thereof.
  • the second wall trailing edge is disposed at least partially inside the lip, wherein a substantial entirety of the vane between an outer surface of the second wall and an outer surface of the bulb portion is rounded.
  • the stem is configured to be disposed in a corresponding opening of the manifold plurality of openings, and includes an aperture providing communication between the manifold and the plenum.
  • the guide vane assembly includes an annular casing, a plurality of vanes, and an air source.
  • the annular casing includes a manifold and a plurality of openings in communication with the manifold.
  • the plurality of vanes is coupled to and extend radially inwardly from the annular casing and defines at least one flow passage therebetween.
  • Each vane includes a first wall, a second wall, a leading edge, a first wall trailing edge, a second wall trailing edge, and a stem.
  • the first and second walls are coupled at the leading edge and spaced apart to define a plenum therebetween.
  • the first and second wall trailing edges are spaced apart to define a gap therebetween.
  • the first wall trailing edge includes a lip extending therefrom toward the second wall, and the second wall trailing edge includes a bulb section extending along at least a portion of a length thereof.
  • the second wall trailing edge is disposed at least partially inside the lip, wherein a substantial entirety of the vane between an outer surface of the second wall and an outer surface of the bulb portion is rounded.
  • the stem is configured to be disposed in a corresponding opening of the manifold plurality of openings, and includes an aperture providing communication between the manifold and the plenum.
  • the air source is in flow communication with the annular casing plenum and is configured to selectively supply air thereto to thereby provide air to the vane plenum and vane gap such that when air flows through the flow passage in a first direction, air flowing through the vane gap redirects the flow passage air to flow in a second direction.
  • FIG. 1 is a cross section view of an exemplary gas turbine engine
  • FIG. 2 is a cutaway view of an exemplary inlet guide vane assembly that may be implemented into the fan module of FIG. 1 ;
  • FIG. 3 is an isometric view of an exemplary vane that may be implemented into the inlet guide vane assembly shown in FIG. 2;
  • FIG. 4 is a cutaway view of the vane shown in FIG. 3;
  • FIG. 5 is a cross section view of the vane shown in FIG. 3;
  • FIG. 6 is a close up view of a trailing section of the exemplary vane of FIG. 5.
  • the turbofan jet engine 100 includes a fan module 110, a compressor module 120, a combustor and turbine module 130 and an exhaust module 140.
  • the fan module 110 is positioned at the front, or "inlet" section of the engine 100, and includes an inlet guide vane assembly 106 that directs a primary airflow 202 (shown in FIG. 2) into the fan module 110.
  • the fan module 110 also includes a fan 108 that induces air from the surrounding environment into the engine 100.
  • the fan module 110 accelerates a fraction of this air as the primary airflow 202 toward the compressor module 120, and the remaining fraction is accelerated into and through a bypass 112, and out the exhaust module 140.
  • the compressor module 120 raises the pressure of the air it receives to a relatively high level.
  • the compressor module 120 includes a low pressure section 150 and a high pressure section 160 through which the primary airflow 202 (shown in FIG. 2) travels.
  • the low pressure section 150 typically includes stages, each of which includes rotors 170 and guide vane assemblies 175.
  • Each of the rotors 170 has a plurality of blades (not shown) and is rotationally mounted on a low pressure shaft 190, which is driven by the low pressure turbine 116. As the rotors 170 rotate, the blades force primary airflow 202 through each of the guide vane assemblies 175 in subsequent sections.
  • Each guide vane assembly 175 also includes a plurality of vanes.
  • the high-pressure compressed air then enters the combustor and turbine module 130, where a ring of fuel nozzles 114 (only one illustrated) injects a steady stream of fuel.
  • the injected fuel is ignited by a burner (not shown), which significantly increases the energy of the resulting high-pressure compressed gases.
  • the high-energy compressed gases then flow first into a high pressure turbine 115 and then a low pressure turbine 116, causing rotationally mounted turbine blades 118 on each turbine 115, 116 to turn and generate energy.
  • the energy generated in the turbines 115, 116 is used to power other portions of the engine 100, such as the fan module 110 and the compressor module 120.
  • the gases exiting the combustor and turbine module 130 then leave the engine 100 via the exhaust module 140.
  • FIG. 2 a cutaway view of an exemplary inlet guide vane assembly 200 is shown.
  • the inlet guide vane assembly 200 may be used in the fan module 110 as inlet guide vane assembly 106 or in the compressor module 120 for guide vane assembly 175.
  • the inlet guide vane assembly 200 is configured to direct a primary airflow 202 through a flow passage in a desired direction.
  • the guide vane assembly 200 includes an annular casing 204 and, as briefly mentioned above, a plurality of vanes 206.
  • the annular casing 204 has a manifold 208 and a plurality of openings 210 (one of which is shown) formed therein, and both are in flow communication with a non-illustrated secondary air flow source.
  • the openings 210 which fluidly communicate with the manifold 208, are configured to suitably receive the vanes 206.
  • Each vane 206 includes an airfoil 304, a platform 306, and a stem 308.
  • the platform 306 is configured to radially contain engine airflow and position the vane 206 in the primary flow path 202.
  • the stem 308 attaches the vane 206 to the annular casing 204 and includes one or more apertures 310 formed therein that communicate with the annular casing manifold 208.
  • the stem 308 is shown with a cylinder 312 configuration machined therein, it will be appreciated that in other embodiments, any one of numerous other shapes suitable for attaching the vane 206 to the annular casing 204. Referring now to FIGs.
  • the airfoil 304 has two walls 314, 316, a leading edge 320, and a trailing section 324.
  • the walls 314, 316 are spaced apart from one another to define a plenum 318 therebetween and are joined together at the leading edge 320.
  • the plenum 318 is configured to direct a secondary airflow 212 received from the stem aperture 310 therethrough.
  • standoffs 322 may be disposed in the plenum 318 to direct the secondary airflow 212 in a desired direction.
  • the standoffs 322 extend between the two walls 314, 316 and may have any shape that affects the secondary airflow 212 in a desired manner.
  • the walls 314, 316 and leading edge 320 are substantially smooth so that the primary airflow 202 traveling from the leading edge 320 toward the trailing section 324 flows substantially along the outer surface of the walls 314, 316.
  • the secondary air source provides secondary air to the annular casing plenum 208, which travels through the vane plenum 318, and exits the trailing section 324.
  • the gap 328 is defined by trailing edges 330, 332 that are formed on each of the walls 314, 316.
  • the trailing edge 330 of the first wall 314 preferably extends past the trailing edge 332 of the second wall 316.
  • the first wall trailing edge 330 includes a lip 334 that extends along substantially an entire length thereof and projects toward the second wall 316.
  • the lip 334 may have a blunt edge, as shown in FIGs.
  • the second wall trailing edge 332 includes a bulb portion 336 that extends the length thereof.
  • the bulb portion 336 is disposed inside of and is at least partially surrounded by the lip 334.
  • a substantial entirety of the vane 206 between an outer surface of the second wall 316 and an outer surface of the bulb portion 336 is rounded.
  • a substantial entirety of the vane 206 between an inner surface of the second wall 316 and inner surface of the bulb portion 336 may also be smooth.
  • the primary airflow 202 flows along the outer surfaces of the first and second walls 314, 316. Because of the features of the trailing edge section as described above, the primary airflow 202 "stays attached" to the outer surfaces walls 314, 316.
  • the secondary airflow 212 interacts with the primary airflow 202. Consequently, the direction in which the primary airflow 202 travels is altered from a first direction to a second direction.
  • the amount of directional change may be modified by adjusting the amount of air supplied by the secondary air supply source to the secondary airflow 212. Thus, if a small amount of air is provided, the secondary airflow 212 will cause a slight change in primary airflow 202 direction. If a larger amount of air is supplied, the change in the primary airflow 202 direction will be more affected.
  • the guide vane assembly may be retrofitted into currently existing gas turbine engines, or implemented in the design of new gas turbine engines. Additionally, the guide vane assembly redirects primary airflow by using a secondary airflow to interact therewith. Specifically, the secondary airflow remains attached to the rounded surface of the bulb portion of the trailing edge by a Coanda effect, changing the flow separation point and lift force acting on each vane. The change in lift force redirects the primary airflow by adding a swirl component transverse thereto.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un ensemble d'aubes de guidage comprenant un carter annulaire et des aubes qui sont couplées au carter annulaire, et qui s'étendent radialement vers l'intérieur à partir de celui-ci. Chaque aube comprend une première paroi, une seconde paroi, un bord d'attaque, un bord de fuite de première paroi, et un bord de fuite de seconde paroi. Les première et seconde parois sont couplées au niveau du bord d'attaque, et espacées pour définir un espacement entre celles-ci. Les bords de fuite sont espacés pour définir un intervalle entre ceux-ci. Le bord de fuite de la première paroi comprend une lèvre s'étendant à partir de celui-ci vers la seconde paroi, et le bord de fuite de la seconde paroi comprend une section de bulbe s'étendant le long d'au moins une partie de sa longueur. Le bord de fuite de la seconde paroi est disposé au moins partiellement à l'intérieur de la lèvre, sensiblement l'intégralité de l'aube entre une surface extérieure de la seconde paroi et une surface extérieure de la partie de bulbe étant arrondie.
EP07868284A 2006-05-18 2007-05-18 Technique de contrôle d'écoulement pour guider un écoulement en vrac vectoriel quittant une aube Withdrawn EP2019924A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US80133806P 2006-05-18 2006-05-18
US49465106A 2006-07-26 2006-07-26
PCT/US2007/069200 WO2008057627A2 (fr) 2006-05-18 2007-05-18 Technique de contrôle d'écoulement pour guider un écoulement en vrac vectoriel quittant une aube

Publications (1)

Publication Number Publication Date
EP2019924A2 true EP2019924A2 (fr) 2009-02-04

Family

ID=39345270

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07868284A Withdrawn EP2019924A2 (fr) 2006-05-18 2007-05-18 Technique de contrôle d'écoulement pour guider un écoulement en vrac vectoriel quittant une aube

Country Status (3)

Country Link
EP (1) EP2019924A2 (fr)
CA (1) CA2652708A1 (fr)
WO (1) WO2008057627A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007029367A1 (de) * 2007-06-26 2009-01-02 Rolls-Royce Deutschland Ltd & Co Kg Schaufel mit Tangentialstrahlerzeugung am Profil

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935245A (en) * 1956-12-10 1960-05-03 Westinghouse Electric Corp Gas reaction rotors
DE1043573B (de) * 1957-01-09 1958-11-13 Stork Koninklijke Maschf Zentrifugalgeblaese mit einem Laufrad, in welches das Foerdermittel auf beiden Seiten des Rades eintritt
US2874894A (en) * 1957-03-01 1959-02-24 Westinghouse Electric Corp Gas reaction rotors
US2920813A (en) * 1958-01-02 1960-01-12 Westinghouse Electric Corp Gas reaction rotors
US3830450A (en) * 1972-12-15 1974-08-20 Us Navy Dual purpose circulation control airfoil
US3992880A (en) * 1975-08-07 1976-11-23 The Garrett Corporation Variable capacity torque converter and method
US4222703A (en) * 1977-12-13 1980-09-16 Pratt & Whitney Aircraft Of Canada Limited Turbine engine with induced pre-swirl at compressor inlet

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008057627A3 *

Also Published As

Publication number Publication date
CA2652708A1 (fr) 2008-05-15
WO2008057627A3 (fr) 2008-07-10
WO2008057627A2 (fr) 2008-05-15

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