WO2013187936A1 - Régulation de flux de fabrication d'additif - Google Patents

Régulation de flux de fabrication d'additif Download PDF

Info

Publication number
WO2013187936A1
WO2013187936A1 PCT/US2013/020313 US2013020313W WO2013187936A1 WO 2013187936 A1 WO2013187936 A1 WO 2013187936A1 US 2013020313 W US2013020313 W US 2013020313W WO 2013187936 A1 WO2013187936 A1 WO 2013187936A1
Authority
WO
WIPO (PCT)
Prior art keywords
additive manufacturing
integral part
recited
cavity
passage
Prior art date
Application number
PCT/US2013/020313
Other languages
English (en)
Inventor
Brian Boyce
Original Assignee
Pratt & Whitney Rocketdyne, 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 Pratt & Whitney Rocketdyne, Inc. filed Critical Pratt & Whitney Rocketdyne, Inc.
Publication of WO2013187936A1 publication Critical patent/WO2013187936A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/78—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant

Definitions

  • the present disclosure relates to additive manufacturing techniques, and more particularly to a flow control manufactured thereby.
  • Rocket engines deliver fuel and oxidizer to a combustion chamber through an injector assembly where the propellants are atomized, mixed, and combusted. Certain rocket engines adjust the quantity of propellant injected into the combustion chamber yet maintain propellant pressures across the injector assembly.
  • the injector assembly has a relatively large internal volume and may potentially generate combustion instabilities and back flow under transient operations.
  • Figure 1 is a general longitudinal schematic sectional view of an exemplary rocket engine
  • Figure 2 is an expanded schematic sectional view of an injector assembly illustrating a single injector according to one non-limiting embodiment
  • Figure 3 is an expanded schematic sectional view of a flow control assembly according to one non-limiting embodiment.
  • Figure 1 illustrates a general schematic view of a rocket engine 10.
  • the engine 10 generally includes a nozzle assembly 12, a fuel system 14, an oxidizer system 16 and an ignition system 18.
  • a combustion chamber wall 20 along a thrust axis A generally defines a thrust chamber 22, a combustion chamber 24 upstream of the thrust chamber 22, and a combustion chamber throat 26 therebetween.
  • a particular rocket engine 10 is schematically illustrated it should be appreciate that various other rocket engine, aero engines, ramjets and other combustion systems will also benefit hereby.
  • An injector assembly 28 includes a multitude of fuel/oxidizer injector elements 30 that communicate through an injector face 32 into the combustion chamber 24.
  • the fuel/oxidizer injector elements 30 receive fuel via a fuel manifold 34 in communication with the fuel system 14 and an oxidizer manifold 36 in communication with the oxidizer system 16.
  • the fuel manifold 34 may receive fuel that may first traverse through the combustion chamber wall 20 to facilitate cooling of the nozzle assembly 12.
  • the injector assembly 28 generally includes a faceplate 40 and an inter-propellant plate 42 which separates the fuel manifold 34 and the oxidizer manifold 36.
  • the faceplate 40 includes numerous fuel sleeves 44 through which a conduit 46 from the inter-propellant plate 42 passes.
  • the fuel sleeves 44 includes a multiple of apertures 48 that communicate with an annulus 50 that surrounds the conduit 46 and is open to the combustion chamber 24.
  • the inter-propellant plate 42 defines an additive manufacture support structure 52 having a cavity 54 therein that may, for example, communicate with a first passage 56 and a second passage 58. That is, the additive manufacture support structure 52 may form all or part of the inter-propellant plate 42 within which the cavity 54 is defined.
  • the first passage 56 may extend through a boss 60 on the oxidizer manifold 36 side of the inter-propellant plate 42 and the second passage 58 may be in communication with the conduit 46. It should be appreciated that additional passages may also be in communication with the cavity 54.
  • a non-integral part 62 such as a conical check valve prevents back flow from the combustion chamber 24.
  • the cavity 54, non-integral part 62 and passages 56, 58 define a flow control device for each injector element 30 of the inter-propellant plate 42.
  • an additive manufacturing process beneficially permits ready incorporation during manufacture.
  • One additive manufacturing process includes powder bed metallurgy in which layers of powder alloy such as Inconel or other material is sequentially build-up by systems from, for example, Concept Laser of Lichtenfels, DE and EOS of Kunststoff, DE.
  • the cavity 54 is formed with the non-integral part 62 movably manufactured therein by selectively non-fusing of powder in at least some locations where the non-integral part 62 would otherwise abut the supporting structure such as the conduit 46.
  • a layer of powder may be selectively not fused to render the non-integral part 62 free to move within the cavity 54.
  • non-integral is defined as not connected to the support structure 52, however, even a slight connection may result in manufacture of the non-integral part 62 that then breaks away in use.
  • the additive manufacture support structure 52 is then completed such that the non-integral part 62 has a geometry that could not escape from the cavity 54 even through the largest passage 56, 58.
  • the non-integral part 62 is trapped within, but remains free to move or float, within the cavity 54 without the potential for leakage from an assembled structure.
  • the non-integral part 62 in the disclosed non-limiting embodiment may be corneal in shape with a tip 64 directed into an inflow passage to, for example, reduce back flow.
  • the geometry of the non-integral part 62 may be selected based on the particular application.
  • the shape of the non-integral part may be akin to a reed, it may be rectangular boxed, cylindrical or other.
  • the non-integral part 62 may rest upon a seat 66 within the cavity 54. The non-integral part 62 may thereby be positioned at particular locations at predefined operational conditions.
  • the additive manufacture support structure 52 may be incorporated in other machines.
  • air-breathing engines or other systems may include, but are not limited to, tubes, conduits, flow bodies, vessels and other structures from which integral flow-control elements may benefit.
  • various non-integral parts such as swirl elements, diffusers, atomization nozzles, beads, obstructions, catalysts, and others will also benefit herefrom.
  • another disclosed, non-limiting embodiment includes a multiple of non-integral parts 62' contained within a cavity 54'.
  • the multiple of non-integral parts 62' may be spheres or other shapes that facilitate agitation of a fluid such as a propellant which passes through the cavity 54'.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

Selon l'invention, un appareil comprend une enveloppe de fabrication d'additif qui définit au moins en partie une cavité et un passage en communication fluidique avec celle-ci et une partie non intégrée de fabrication d'additif placée de façon mobile dans ladite cavité, la partie non intégrée définissant une géométrie qui ne peut pas passer par ledit passage.
PCT/US2013/020313 2012-06-15 2013-01-04 Régulation de flux de fabrication d'additif WO2013187936A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261660562P 2012-06-15 2012-06-15
US61/660,562 2012-06-15

Publications (1)

Publication Number Publication Date
WO2013187936A1 true WO2013187936A1 (fr) 2013-12-19

Family

ID=49758586

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2013/020313 WO2013187936A1 (fr) 2012-06-15 2013-01-04 Régulation de flux de fabrication d'additif

Country Status (1)

Country Link
WO (1) WO2013187936A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017062408A1 (fr) * 2015-10-05 2017-04-13 Vector Launch Inc. Moteur-fusée à oxygène-propylène liquide amélioré
US10527003B1 (en) 2015-04-12 2020-01-07 Rocket Lab Usa, Inc. Rocket engine thrust chamber, injector, and turbopump
US10557732B2 (en) 2017-12-07 2020-02-11 Cameron International Corporation Flowmeters and methods of manufacture
US10852173B2 (en) 2018-12-18 2020-12-01 Sensia Llc Flowmeters and methods of manufacture

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4812071A (en) * 1986-08-27 1989-03-14 Batra Pran Correction fluid pen
US4863538A (en) * 1986-10-17 1989-09-05 Board Of Regents, The University Of Texas System Method and apparatus for producing parts by selective sintering
US5222361A (en) * 1988-08-03 1993-06-29 Nelson Daniel E Rocketjet engine
US20090269497A1 (en) * 2008-04-28 2009-10-29 The Boeing Company Built-up composite structures with a graded coefficient of thermal expansion for extreme environment applications
US20110135952A1 (en) * 2009-12-04 2011-06-09 Honeywell International Inc. Turbine components for engines and methods of fabricating the same
US20110219743A1 (en) * 2010-03-12 2011-09-15 United Technologies Corporation Injector assembly for a rocket engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4812071A (en) * 1986-08-27 1989-03-14 Batra Pran Correction fluid pen
US4863538A (en) * 1986-10-17 1989-09-05 Board Of Regents, The University Of Texas System Method and apparatus for producing parts by selective sintering
US5222361A (en) * 1988-08-03 1993-06-29 Nelson Daniel E Rocketjet engine
US20090269497A1 (en) * 2008-04-28 2009-10-29 The Boeing Company Built-up composite structures with a graded coefficient of thermal expansion for extreme environment applications
US20110135952A1 (en) * 2009-12-04 2011-06-09 Honeywell International Inc. Turbine components for engines and methods of fabricating the same
US20110219743A1 (en) * 2010-03-12 2011-09-15 United Technologies Corporation Injector assembly for a rocket engine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10527003B1 (en) 2015-04-12 2020-01-07 Rocket Lab Usa, Inc. Rocket engine thrust chamber, injector, and turbopump
US11408375B1 (en) 2015-04-12 2022-08-09 Rocket Labs USA, Inc. Rocket engine turbopump with coolant passage in impeller central hub
US11415082B1 (en) 2015-04-12 2022-08-16 Rocket Labs USA, Inc. Turbopump, thrust chamber, and injector with distribution system and a circular array of support columns to flow liquid from the distribution system into a combustion chamber
WO2017062408A1 (fr) * 2015-10-05 2017-04-13 Vector Launch Inc. Moteur-fusée à oxygène-propylène liquide amélioré
US10072612B2 (en) 2015-10-05 2018-09-11 Vector Launch Inc. Enhanced liquid oxygen-propylene rocket engine
US10316795B2 (en) 2015-10-05 2019-06-11 Vector Launch Inc. Liquid oxygen-propylene rocket injector
US10557732B2 (en) 2017-12-07 2020-02-11 Cameron International Corporation Flowmeters and methods of manufacture
US11307070B2 (en) 2017-12-07 2022-04-19 Sensia Llc Ultrasonic flowmeter body formed by additive manufacturing and having plurality of angled connectors for transceivers and radial connectors for supporting reflectors
US10852173B2 (en) 2018-12-18 2020-12-01 Sensia Llc Flowmeters and methods of manufacture

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