US3463402A - Jet sound suppressing means - Google Patents

Jet sound suppressing means Download PDF

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Publication number
US3463402A
US3463402A US605454A US3463402DA US3463402A US 3463402 A US3463402 A US 3463402A US 605454 A US605454 A US 605454A US 3463402D A US3463402D A US 3463402DA US 3463402 A US3463402 A US 3463402A
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United States
Prior art keywords
doors
duct
blow
engine
annular
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Expired - Lifetime
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US605454A
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English (en)
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Chandos E Langston Jr
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RTX Corp
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United Aircraft Corp
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N27/00—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means
    • G01N27/26—Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating electrochemical variables; by using electrolysis or electrophoresis
    • G01N27/403—Cells and electrode assemblies
    • G01N27/404—Cells with anode, cathode and cell electrolyte on the same side of a permeable membrane which separates them from the sample fluid, e.g. Clark-type oxygen sensors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N7/00—Analysing materials by measuring the pressure or volume of a gas or vapour
    • G01N7/10—Analysing materials by measuring the pressure or volume of a gas or vapour by allowing diffusion of components through a porous wall and measuring a pressure or volume difference

Definitions

  • a gas turbine engine having an exhaust iiow means which will reduce the perceived noise level associated with the discharge of a high velocity gas jet or jets.
  • An exhaust duct having flaps at the rear end thereof having a pod thereon onto which blow-in doors are pivotally mounted to open inwardly toward said duct.
  • An annular body being positioned rearwardly of said pod with its inner surface forming an inlet passageway with each blow-in door when it is in its inward position.
  • Nozzles means are located in the annular body for a balance between engine performance and noise suppression. Means are provided for inducing turbulence where the blow-in doors end in an inward position. Said turbulence inducing means can comprise means for directing a gas flow into said passageways or involve some other devices which project into said passageways.
  • This invention relates to means for reducing the perceived noise level associated with the discharge, usually through an ejector shroud, of a high velocity gas jet or jets primarily from a gas turbine engine.
  • the exit area of said ejector being Set in or adjusted to an optimum position to obtain the most favorable balance between noise attenuation and nozzle performance.
  • FIGURE l is a longitudinal schematic view of the exhaust section of a jet engine showing the invention.
  • FIGURE 2 is a view showing a modification of FIG URE l which provides an annular liange to permit airow around a nozzle at the end of a ramp.
  • FIGURE 3 is an enlarged view showing a mechanism for varying the direction of an air jet around a nozzle.
  • FIGURE 4 is a view taken along the line 4-4 of FIG- URE 3 while also showing the slots.
  • FIGURE 5 is a view showing a modification of FIG- URE 2 which provides an annular flange to permit airflow around the nozzle and provides an annular trip extending into the outer airfioW.
  • FIGURE 6 is a view showing a modification of FIG- URE l with the ramp leading into the nozzle having a roughened surface.
  • FIGURE 7 is a view showing a modification of FIG- URE l wherein a second attaching surface is fixed to the converging nozzle portion.
  • FIGURE 8 is a view showing the invention applied to an engine having two primary gas liows, one through an inner duct and one through an annular duct around said inner duct.
  • FIGURE l shows the rear end of a conventional high speed aircraft jet engine 12.
  • Engine 12 is of a conventional design and may be of the type described more fully in vU.S. Patent No. 2,747,367.
  • the primary duct 26 has at its downstream end an eX- haust nozzle 48 forming an outlet. While the exhaust nozzle 48 is shown consisting of a number of sectioned pieces 10 positioned at a fixed angle, this exhaust nozzle 48 may be made up of movable aps so sectioned and adapted to move to other positions (note U.S. Patent Nos. 3,062,003; 2,815,643 and 2,836,034).
  • the exhaust nozzle 48 is shown fixed in this position since it is in this position during takeoff, and other times demanding high power, and it is at this time that noise attenuation is most desirable.
  • the manifold is consrtucted having a raised center so that a step is formed where the blow-in doors 44 end, and the flaps 10 for nozzle 48 begin, to start the flow separation.
  • the engine 12 has a nacelle or pod 34 around it with a fixed member 40 positioned axially downstream of the nacelle or pod 34.
  • This xed member 40 can be supported from means associated with the engine such as by a plurality of axially extending struts, or the fixed member 40 can be attached to parts of the aircraft structure.
  • a plurality of sealably, overlapping, and circumfcrentially positioned pivotal blow-in doors 44 are positioned between the end of pod 34 and the forward part of fixed member 40. In their outermost position, the blow-in doors extend between the end of the pod 34 and the forward part of fixed member 40 to provide a continuation of the pod 34 to the outer surface 84 of the fixed member 4).
  • blow-in doors 44 move inwardly until their rear ends touch or nearly touch the rear portion of the engine at the top of the raised manifold 32 adjacent the attachment -point of the flaps 48 forminga step. While the blow-in doors 44 and the flaps 46 extending from the rearward end of the fixed member 40 are shown as free floating, they may be power actuated.
  • the nozzle 48 is the primary nozzle and the nozzle .formed by the fixed member 40 and aps 46 is the secondary nozzle. As seen in FIGURE l, the primary nozzle 48 has its flaps 10 positioned inwardly and the blow-in doors are located inwardly with the rear ends thereof positioned against the manifold 32 thereby forming an annular inwardly extending ramp while the flaps 46 are angled inwardly.
  • an engine having the elements as shown in FIGURE 1 should have them in the position as shown. That is, the flaps 10 forming the primary nozzle 48 are located essentially as shown, i.e., to form a blunt base region surrounding the nozzle throat (radius r1), and blow-in doors 44 are located in an inward position forming the annular ramp as shown with the inner ends of the doors resting or held on or above the raised portion of the manifold to create a step where the flaps 10 extend inwardly from the end of the duct 26.
  • a turbulent sheer layer is started at the step formed at the end of the duct 26 which grows into the turbulent sheer layer extending from the annular end of the nozzle 48.
  • the rapid growth of the turbulent sheer layer provides sound suppression by reducing the area of the surface over which the sound is being emitted.
  • a gas can be injected through the openings 38.
  • the gas is brought from an inlet pipe 14 through a control 16 and outlet pipe 18 which is connected to the manifold 32.
  • the control 16 can be automatically controlled by an engine parameter such as a power setting, or it can be manually operated if desired.
  • Inlet pipe 14 can be connected to an engine compressor stage or some other source of high pressure gas.
  • FIGURE 2 is a modification of FIGURE 1 wherein the manifold 32 is replaced by a solid annular flange 50 having spaced projections 52 extending therefrom. It can be seen that when the end of blow-in doors 44 engage the tops of the spaced projections S2, space is provided for the injection of a gas which could be directed between the inside of blow-in doors 44 and around the primary duct 26. It can be seen that a more pronounced step is formed by this arrangement.
  • FIGURES 3 and 4 show means for varying the angle at which a gas jet is injected.
  • the exit end of the primary duct 26 is shaped as a polygon with each side having a mounting sleeve 60 with a movable manifold section 62 therein.
  • Adjacent ends of mounting sleeves 60 are connected by Wedge-shaped nieces of conduit 6l which are xed in place and sealed so that iiuid ow can pass between manifold sections ⁇ 62.
  • a plurality of the pieces of conduit 61 have an opening 63 therein which would be connected to a source of gas such as pipe 18.
  • Each mounting sleeve 60 has a large slot 64 extending from a line parallel to the surface of the blow-in door 44 upwardly for a range of about 50 about the centerline of said sleeve.
  • Each movable manifold section has a long narrow slot 66 or a line of holes for directing gas flow from the interior of the section through slot 64.
  • An arm 70 extends from the center of each manifold section 62 forwardly through an opening 72 in each sleeve member 60.
  • An elongated slot 74 is located along the free end of each arm 70.
  • a bell crank 76 mounted for pivotal movement to the top of a bracket 78 fixed to duct 26 has one arm 80 with a pin 82 which rides in the slot 74.
  • the other arm 86 of the bell crank lever is pivotally connected to a tab on a synchronizing ring 88.
  • the ring 88 is moved backwards and forward in accordance with movements of a plurality of links 90.
  • FIGURE 5 is a modification of FIGURE 2 where the rearward part of the tops of projections 52 have an annular projection 53 extending outwardly therea-round to form a trip at that location to further aid in starting flow separation and increasing turbulence.
  • An annular fla-nge 101 extends around the outer end of duct 26 having a sealing material 103 around the outer edge. As the blowin doors come inwardly, they cont-act the sealing material 103 along their length and the ends rest against the projections 52. Gas can be injected into the chamber formed by the duct 26, blow-in doors 44, fiange 50, and flange 101 through openings in the flange 101. As in FIGURE 1, the pipes 18 can be connected thereto.
  • FIGURE 6 differs from FIGURE 1 in that the downstream portion of the outer surface of each blow-in door is roughened as at 45.
  • the roughening need not be too severe. This roughening provides an additional means for creating turbulence.
  • FIGURE 7 adds a second attaching surface to each flap 10 of the nozzle 48 so that when the fiaps are in their innermost position, a surface is formed around the nozzle so that the flow which separates at the rear end the ramp formed by blow-in doors 44 will attached thereto and then separate again. This action increases the level of turbulence as desired to promote rapid growth of the sheer layer surrounding the expanding jet.
  • FIGURE 8 shows the incorporation of applicants device on an engine such as shown in U.S. Patent No. 3,338,051.
  • This engine is of a type wherein an annular duct extending rearwardly from the fan of a fan engine includes a duct burner wherein heat is added to the bypass air for increasing augmentation of the stream.
  • An engine of this type has two primary gas iows, one from the conventional jet engine and one from the surrounding annular duct burner.
  • the engine shown has an annular duct 6 formed by an outer wall 8 and an inner wall 12.
  • the inner wall 12 extends around a jet engine or gas generator having an outer wall 20 with a center cone 22 positioned therein by struts 24.
  • the end of the outer wall 20 forms a converging-diverging section and the rear part of the inner wall 12 of duct 6 ends in a plug surface along which the gas fiowing through duct 6 expands as in a conventional plug nozzle.
  • the rear end of each of these walls, 12 and 20, are connected by an annu; lar blunt base 28,
  • a track mechanism 30 is located in a fixed position around the end of the outer wall 8 which has a plurality of flaps 33 slidably mounted thereon to provide a nozzle capable of having its converging angle varied.
  • An actuator (not shown) provides movement of rods 31.
  • a pod or nacelle 35 encircles the engine and has a plurality of blow-in doors 37.
  • the blow-in doors 37 are constructed of two parts, a forward section 37a and a rearward section 37b. The front part of each forward section 37a is pivoted at the rear of the pod or nacelle 3S.
  • An annular fixed member, or shroud, 39 is spaced downstream from the pod 35 so that the forward edge thereof is adjacent the trailing edges of the blow-in doors when they are in their outermost position completing the outer pod surface (dotted position in FIG. 8). Flaps 41 are pivotally attached to the rearward end of the annular member 39 to change the exit opening. Asshown, the rear part of a section 37a and the forward part of a section 37b are pivotally connected at 54. The hinge point of each blow-in door has a roller 56 at each side which travels in a cam opening which is part of the connecting linkage between all of the blow-in doors and the two clamshells 43 of a clamshell nozzle which is mounted within the annular member, or shroud, 39.
  • a linkage (not shown) between the two clamshells 43 and the blow-in doors could be used which permits the :movement of the blow-in doors between the solid position shown in FIGURE 8 and the dotted position to move the clamshells between their solid position and their dotted position.
  • the solid position of the blow-in doors 37, clamshells 43, and flaps 41 represents their location when the engine is in subsonic Hight and the position of the members is dotted outline shows their respective locations during supersonic flight.
  • a turbulence inducing means is provided in each of walls 12 and 20 upstream of the blunt base 28 to increase the rate of growth of the turbulent sheer layer which lies between the gas generator discharge stream Iand the fan stream over and above that which would result from the blunt base 28 alone.
  • the turbulence inducing means shown consists of slots or holes 45 and 47 to which a gas can be directed by a plurality of pipes 49 and 51, respectively. Pipes 49 and 51 are connected to an annular manifold 58 which is fed from a source of gas under pressure by conduit 55.
  • a turbulence inducing means is provided to induce a turbulent region leaving the blowin doors 37.
  • the turbulence inducing means shown is an annular manifold 57 xed to the rear of the track mechanism 30 with openings 59. This manifold 57 is fed a gas under pressure in the same manner as manifold 53.
  • the clamshells 43 could be power actuated so that they could be placed in a predetermined position to achieve the optimum balance referred to above.
  • the aps 41 could be power actuated so that they could be placed in a predetermined position to achieve the optimum balance referred to above.
  • the precise positioning of the blow-in doors, clamshells and flaps 41 can only be given for a specific engine. The positioning of these elements will vary from engine to engine. It would be necessary to actually have tests made of a particular engine to determine precise positioning of the blow-in doors, clamshells and flaps to achieve desired positions for maintaining a proper balance between performance and noise.
  • trailing edge flaps being connected to the downstream end of the annular member
  • (j) means for inducing turbulence where the blow-in doors end in an inward position.
  • said turbulence inducing means includes means for directing a ow of fluid rearwardly adjacent the ends of the blow-in doors to mix with uid ow passing throuhg the openings made by said blow-in doors.
  • said turbulence inducing means comprises an annular manifold fixedly positioned adjacent the end of said annular duct having openings directed rearwardly along the underside of the blow-in doors.
  • (k) means are provided for directing a flow of fluid rearwardly over the outer edge of the blunt end of the lirst duct.
  • (k) means are provided for directing a ow of uid along the inner edge of the blunt end of the first duct.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being movable inwardly to a point adjacent said flaps
  • annular body having nozzle sections mounted therein which are movable to vary their position in forward tiight to provide an optimum balance between engine performance and noise suppression.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being movable inwardly to a point adjacent said flaps
  • said turbulence inducing means including a preroughenend surface on the downstream surface of the blow-in doors facing the annular body.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being inwardly to a point adjacent said llaps
  • said turbulence inducing means including a radially extending flange adjacent the end of the blow-in doors which extend outwardly into the inlet passageways.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being movable inwardly to a point adjacent said flaps
  • said turbulence inducing means including a builtup surface located midway on the outside of each flap downstream from the ends of said blow-in doors to provide a second attaching surface area for holding the flow from the lower portion of the ow passing through the inlet passageways.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being movable inwardly to a point adjacent said aps.
  • said second duct having an elfective blunt end to separate flow passing through said duct for exhaust gas liow and said second duct.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, positioned inwardly to a point adjacent said flaps
  • a raised abutment having channel cuts in the ⁇ top thereof extends radially outwardly from the end of the duct so that the free end of the blow-in doors will contact it in an inward position.
  • an engine having:
  • blow-in doors pivotally mounted at the end of said pod and extending rearwardly, said doors being movable inwardly -to a point adjacent said aps,
  • said directing means having opening means through which the lthird gas flow passes.
  • said means for directing a third flow of gas being movable so that the angle of iiow can be changed relative to the position of the end of the blow-in doors.
  • the downstream end of the raised abutment has a solid flange extending upwardly so that when the blow-in doors are resting on the abutment, the flange enters into each inlet passageway formed by the blow-in doors.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
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  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
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  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • Molecular Biology (AREA)
  • Exhaust Silencers (AREA)
  • Apparatus Associated With Microorganisms And Enzymes (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
US605454A 1966-12-28 1966-12-28 Jet sound suppressing means Expired - Lifetime US3463402A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US60545466A 1966-12-28 1966-12-28
GB828/67A GB1215446A (en) 1966-12-28 1967-01-06 Apparatus for measuring or detecting dissolved oxygen and process employing said apparatus

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BE (1) BE709007A (enrdf_load_stackoverflow)
DE (1) DE1626148B1 (enrdf_load_stackoverflow)
FR (2) FR1553178A (enrdf_load_stackoverflow)
GB (2) GB1215446A (enrdf_load_stackoverflow)

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US3575261A (en) * 1969-10-24 1971-04-20 Rohr Corp Fan jet silencer with fluid mixture
US3578106A (en) * 1969-10-15 1971-05-11 Rohr Corp Turbofan propulsion silencing apparatus
US3635308A (en) * 1969-07-03 1972-01-18 Rohr Corp Sound suppression system
US3648800A (en) * 1970-04-27 1972-03-14 Gen Electric Coanda expansion exhaust nozzle suppressor
US3655009A (en) * 1969-09-18 1972-04-11 Rohr Corp Method and apparatus for suppressing the noise of a fan-jet engine
US3667680A (en) * 1970-04-24 1972-06-06 Boeing Co Jet engine exhaust nozzle system
US3711013A (en) * 1971-04-26 1973-01-16 Rohr Corp Thrust control and sound apparatus
US3726091A (en) * 1971-02-16 1973-04-10 Rohr Corp Sound suppressing apparatus
US3739984A (en) * 1971-08-25 1973-06-19 Rohr Industries Inc Thrust augmenting and south suppressing apparatus and method
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JP2007187161A (ja) * 2006-01-13 2007-07-26 Snecma 超音速航空機のターボファンジェットエンジン用の、可変領域を有するコア排気ミキサ
RU2326259C1 (ru) * 2007-04-24 2008-06-10 Московский авиационный институт (государственный технический университет) Высотное сопло лаваля
US8192158B1 (en) 2008-12-12 2012-06-05 Mainstream Engineering Corp. Apparatus and method to increase total-to-static pressure ratio across a turbine
US8225592B1 (en) * 2003-06-09 2012-07-24 Florida State University Research Foundation Microjet noise suppression system for jet engines
US8480361B1 (en) 2010-01-26 2013-07-09 Mainstream Engineering Corporation Enhanced system and method to increase the total-to-static pressure ratio across a RAM air turbine using surface contoured flow agitators
US8794902B1 (en) 2010-01-26 2014-08-05 II Daniel K. Van Ness System and method to improve the exhaust pressure across a RAM air turbine through secondary flow mixing

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DE19642393A1 (de) * 1996-10-14 1998-04-16 Mtu Muenchen Gmbh Turbostrahltriebwerk mit einem Blütenmischer
DE102007036527B4 (de) 2007-08-02 2009-07-09 Eads Deutschland Gmbh Düsenanordnung für ein Gasturbinentriebwerk
RU2413161C1 (ru) * 2009-12-28 2011-02-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Устройство для снижения инфракрасной и радиолокационной заметности газотурбинного двигателя
GB201412189D0 (en) 2014-07-09 2014-08-20 Rolls Royce Plc A nozzle arrangement for a gas turbine engine
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US3655009A (en) * 1969-09-18 1972-04-11 Rohr Corp Method and apparatus for suppressing the noise of a fan-jet engine
US3578106A (en) * 1969-10-15 1971-05-11 Rohr Corp Turbofan propulsion silencing apparatus
US3575261A (en) * 1969-10-24 1971-04-20 Rohr Corp Fan jet silencer with fluid mixture
US3667680A (en) * 1970-04-24 1972-06-06 Boeing Co Jet engine exhaust nozzle system
US3648800A (en) * 1970-04-27 1972-03-14 Gen Electric Coanda expansion exhaust nozzle suppressor
US3726091A (en) * 1971-02-16 1973-04-10 Rohr Corp Sound suppressing apparatus
US3711013A (en) * 1971-04-26 1973-01-16 Rohr Corp Thrust control and sound apparatus
US3806035A (en) * 1971-07-06 1974-04-23 Rolls Royce 1971 Ltd Jet propulsion power plant
US3739984A (en) * 1971-08-25 1973-06-19 Rohr Industries Inc Thrust augmenting and south suppressing apparatus and method
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US3826331A (en) * 1972-02-29 1974-07-30 Bolt Beranek & Newman Method of and apparatus for reducing sound generated by surfaces in fluid jet streams and the like
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JPS51131099A (en) * 1975-05-06 1976-11-15 Toshio Horiuchi Silencer making use of the turbulence of fluid
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US5761900A (en) * 1995-10-11 1998-06-09 Stage Iii Technologies, L.C. Two-stage mixer ejector suppressor
US5884472A (en) * 1995-10-11 1999-03-23 Stage Iii Technologies, L.C. Alternating lobed mixer/ejector concept suppressor
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US5884843A (en) * 1996-11-04 1999-03-23 The Boeing Company Engine noise suppression ejector nozzle
US5941065A (en) * 1996-11-04 1999-08-24 The Boeing Company Stowable mixer ejection nozzle
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
US5826794A (en) * 1997-02-28 1998-10-27 The Boeing Company Aircraft scoop ejector nozzle
US6012281A (en) * 1997-08-18 2000-01-11 United Technologies Corporation Noise suppressing fluid mixing system for a turbine engine
US20040031258A1 (en) * 2002-03-20 2004-02-19 Dimitri Papamoschou Jet engine noise suppressor
US7293401B2 (en) * 2002-03-20 2007-11-13 The Regents Of The University Of California Jet engine noise suppressor
US8225592B1 (en) * 2003-06-09 2012-07-24 Florida State University Research Foundation Microjet noise suppression system for jet engines
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JP2007187161A (ja) * 2006-01-13 2007-07-26 Snecma 超音速航空機のターボファンジェットエンジン用の、可変領域を有するコア排気ミキサ
RU2326259C1 (ru) * 2007-04-24 2008-06-10 Московский авиационный институт (государственный технический университет) Высотное сопло лаваля
US8192158B1 (en) 2008-12-12 2012-06-05 Mainstream Engineering Corp. Apparatus and method to increase total-to-static pressure ratio across a turbine
US8480361B1 (en) 2010-01-26 2013-07-09 Mainstream Engineering Corporation Enhanced system and method to increase the total-to-static pressure ratio across a RAM air turbine using surface contoured flow agitators
US8794902B1 (en) 2010-01-26 2014-08-05 II Daniel K. Van Ness System and method to improve the exhaust pressure across a RAM air turbine through secondary flow mixing

Also Published As

Publication number Publication date
GB1215446A (en) 1970-12-09
BE709007A (enrdf_load_stackoverflow) 1968-07-05
FR1553178A (enrdf_load_stackoverflow) 1969-01-10
DE1626148B1 (de) 1971-05-13
GB1207194A (en) 1970-09-30
FR1553172A (enrdf_load_stackoverflow) 1969-01-10

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