WO2021242229A1 - Chambre de combustion à deux parties - Google Patents

Chambre de combustion à deux parties Download PDF

Info

Publication number
WO2021242229A1
WO2021242229A1 PCT/US2020/034672 US2020034672W WO2021242229A1 WO 2021242229 A1 WO2021242229 A1 WO 2021242229A1 US 2020034672 W US2020034672 W US 2020034672W WO 2021242229 A1 WO2021242229 A1 WO 2021242229A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustor
exhaust manifold
section
pressure
piece body
Prior art date
Application number
PCT/US2020/034672
Other languages
English (en)
Inventor
Peter Kinsman
Jr. Calvin Q. Morrison
Luis A. Rosales
Original Assignee
Aerojet 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 Aerojet Rocketdyne, Inc. filed Critical Aerojet Rocketdyne, Inc.
Priority to PCT/US2020/034672 priority Critical patent/WO2021242229A1/fr
Publication of WO2021242229A1 publication Critical patent/WO2021242229A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/002—Combustion apparatus characterised by the shape of the combustion chamber the chamber having an elongated tubular form, e.g. for a radiant tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/08—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber for reducing temperature in combustion chamber, e.g. for protecting walls of combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • High performance combustors for advanced engines such as axial combustors in engines for aquatic vehicles, include numerous components.
  • the components are highly specialized. In order to meet performance goals, manufacturing requirements, and/or material requirements, the components are separately fabricated and then assembled together to form the end-use combustor.
  • a combustor includes a pressure-containing housing disposed along an axis, and a one-piece body also disposed along the axis.
  • the one-piece body has an exhaust manifold section and a liner section.
  • the exhaust manifold section defines a flow path and the liner section at least partially defining a combustion chamber and extending axially from the exhaust manifold section into the pressure- containing housing.
  • the exhaust manifold section is hermetically sealed to the housing.
  • the liner section loosely abuts the pressure-containing housing at an end opposite the exhaust manifold section.
  • the liner section and pressure-containing housing define an insulation cavity.
  • the liner section includes orifices fluidly coupling the insulation cavity and the combustion chamber.
  • the one-piece body is molybdenum alloy.
  • the one-piece body is ceramic.
  • the pressure- containing housing is a metallic material that is selected from the group consisting of titanium alloy and nickel-chromium-tungsten-molybdenum alloy, and the one-piece body is molybdenum alloy.
  • the pressure- containing housing and the one-piece body are in contact exclusively at first and second joints located, respectively, at a base of the liner at the exhaust manifold section and the end opposite the exhaust manifold section.
  • the pressure- containing housing includes an annular mate face in contact with the liner section in the first joint.
  • the pressure- containing housing includes an expansion gap next to the annular mate face for accommodating thermal expansion of the liner section.
  • the pressure- containing housing includes an annular channel located axially intermediate the first and second joints.
  • a combustor includes a one-piece body disposed along an axis and formed of a refractory material.
  • the one-piece body has an exhaust manifold section and a liner section.
  • the exhaust manifold section defines exhaust channels and the liner section circumscribes a combustion chamber and extends axially from the exhaust manifold section.
  • the refractory material is molybdenum alloy.
  • the refractory material is ceramic.
  • Figure 1 illustrates an example combustor.
  • Figure 2 illustrates another example combustor.
  • Figure 1 schematically illustrates a combustor 20.
  • the combustor 20 may find use in advanced engines for aquatic vehicles, but is not limited thereto.
  • the combustor 20 is of two-piece can architecture.
  • the two-piece architecture of the combustor 20 includes a pressure- containing housing 22 and a one-piece body 24 disposed along an axis A.
  • the pressure- containing housing 22 and the one-piece body 24 are engaged together to form a combustion chamber 26 in which hot gases are generated.
  • the pressure-containing housing 22 and the one-piece body 24 are formed from materials that are able to withstand the exposure temperatures.
  • the pressure-containing housing 22 is formed from a ceramic material, a metallic alloy, such as Inconel-718 or Haynes-230, a titanium alloy, or other high temperature alloy. Such alloys provide good temperature resistance, as well as high strength- to-weight ratio.
  • the one-piece body 24 is generally exposed to higher temperatures than the pressure-containing housing 22 and is thus formed of a refractory material, such as a ceramic material, molybdenum alloy, niobium alloy, tungsten alloy, although the molybdenum alloy provides a useful balance of properties.
  • a refractory material such as a ceramic material, molybdenum alloy, niobium alloy, tungsten alloy, although the molybdenum alloy provides a useful balance of properties.
  • the one-piece body 24 is of unitary construction, as opposed to a group of mechanically attached components that make up an assembly. For instance, all portions of the one-piece body 24 are fused together as one piece.
  • the one-piece body 24 is a monolithic body of the refractory material.
  • the monolithic body is a single, continuous piece, as opposed to a collection of functional parts that are bonded, secured, fused together, or mechanically attached in joints.
  • a monolithic body may be formed by casting, additive manufacturing from a starting powder, machining, or forging or other wrought processing.
  • the pressure-containing housing 22 in this example is comprised of a neck 28, which serves for injection of propellant into the combustion chamber 26, a bulkhead wall 30, and an annular wall 32.
  • the neck 28 may be varied or even excluded, depending on the particular design of the combustor 20.
  • the bulkhead wall 30 extends radially from the neck 28, and the annular wall 32 extends axially from the bulkhead wall 30.
  • the annular wall 32 On its inside diameter surface the annular wall 32 includes a first annular mate face 32a and a second annular mate face 32b, which as described below interface with the one-piece body 24.
  • the one-piece body 24 includes an exhaust manifold section 40 and a liner section 42.
  • the exhaust manifold section 40 defines one or more axial exhaust ports 44 (flow passages).
  • Figure 2 shows the combustor 20 in a varied design in which, rather than the axial exhaust port 44, there is at least one radial exhaust port 144. It is to be further understand that additional variations may include both axial and radial exhaust ports.
  • the axial or radial exhaust ports 44/144 are fluidly connected to the combustion chamber 26 and serve to discharge hot gases from the combustion chamber 26.
  • the exhaust manifold section 40 also includes a torque transmission feature 46, for attachment with a rotatable shaft (not shown).
  • the combustor 20 is rotatable and thus co-rotates with the shaft during operation.
  • the liner section 42 includes an annular liner wall 48 that extends axially from the exhaust manifold section 40 and circumscribes the combustion chamber 26.
  • the annular liner wall 48 extends into the pressure-containing housing 22 and generally serves to shield the annular wall 32 from the hot gases in the combustion chamber 26.
  • the pressure-containing housing 22 and the one-piece body 24 are in contact exclusively at first and second joints 50/52 that are located, respectively, at the base of the annular liner wall 48 (at the exhaust manifold section 40) and an opposed end of the annular liner wall 48 (the free end).
  • the annular liner wall 48 contacts the respective annular mate faces 32a/32b of the annular wall 32.
  • the annular mate faces 32a/32b may serve for mechanical support and piloting to facilitate proper positioning of the annular liner wall 48 with respect to the annular can wall 32.
  • Seals may be provided in or near the annular mate face 32b to hermetically seal the exhaust manifold section 40 and the pressure-containing housing 22 together.
  • a backstop face 54 serves to limit the extent that the annular liner wall 48 projects into the pressure-containing housing 22.
  • the pressure-containing housing 22 does not include a similar backstop but rather an expansion gap 56 axially adjacent the first mate face 32a.
  • the expansion gap 56 permits axial thermal expansion of the annular liner wall 48 to thereby facilitate avoidance of thermal stresses between the can 22 and the one- piece body 24.
  • the annular liner wall 48 encloses an insulation space 58 between its outer diameter surface and the annular channel 34 of the annular wall 32.
  • the insulation space 58 may be cooled through the annular wall 32 in order to facilitate thermal management of the annular liner wall 48.
  • Orifices 60 are provided through the annular liner wall 48 to connect the insulation space 58 with the combustion chamber 26.
  • the orifices 60 are relatively small so as to permit pressure equalization of the insulation space 58 with the combustion chamber 26 but otherwise limit ingress flow of hot gases into the insulation space 58.
  • the high pressure combustion gases that are generated in the combustion chamber 26 expand and immediately fill the insulation space 58 through the orifices 60.
  • the net volume of remaining gas exits the combustion chamber 26 via the axial and/or radial exhaust ports 44/144 and is distributed as high-temperature , high-pressure gas applying direct force in a mechanical system, to create work, downstream of the combustion process.
  • the annular liner wall 48 and the exhaust manifold section 40 are of unitary construction.
  • the unitary construction serves to eliminate seals and additional parts, thereby making the combustor 20 more compact.
  • a manifold piece may be attached by a sealed threaded fastener connection to a liner sleeve.
  • the threaded connection and sealing of that connection are unnecessary, which may also facilitate reductions in leak paths and fabrication steps.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Abstract

L'invention concerne une chambre de combustion comprenant une enveloppe à pression (22) et un corps monobloc (24) disposé le long d'un axe. Le corps monobloc comporte une section de collecteur d'échappement (40) et une section de chemise (42). La section de collecteur d'échappement définit un circuit d'écoulement, et la section de chemise définit, au moins partiellement, une chambre de combustion (26) et s'étend axialement à partir de la section de collecteur d'échappement dans l'enveloppe à pression. La section de collecteur d'échappement est fixée hermétiquement à l'enveloppe. La section de chemise vient en butée de manière lâche contre l'enveloppe à pression, au niveau d'une extrémité opposée à la section de collecteur d'échappement. La section de chemise et l'enveloppe à pression définissent une cavité d'isolation (58).
PCT/US2020/034672 2020-05-27 2020-05-27 Chambre de combustion à deux parties WO2021242229A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2020/034672 WO2021242229A1 (fr) 2020-05-27 2020-05-27 Chambre de combustion à deux parties

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2020/034672 WO2021242229A1 (fr) 2020-05-27 2020-05-27 Chambre de combustion à deux parties

Publications (1)

Publication Number Publication Date
WO2021242229A1 true WO2021242229A1 (fr) 2021-12-02

Family

ID=71094841

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2020/034672 WO2021242229A1 (fr) 2020-05-27 2020-05-27 Chambre de combustion à deux parties

Country Status (1)

Country Link
WO (1) WO2021242229A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417835A (en) * 1936-09-25 1947-03-25 Harry H Moore Combustion device
US2517015A (en) * 1945-05-16 1950-08-01 Bendix Aviat Corp Combustion chamber with shielded fuel nozzle
US2701445A (en) * 1950-09-08 1955-02-08 Armstrong Siddeley Motors Ltd Ignition equipment for the combustion equipment of rocket motors
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2417835A (en) * 1936-09-25 1947-03-25 Harry H Moore Combustion device
US2517015A (en) * 1945-05-16 1950-08-01 Bendix Aviat Corp Combustion chamber with shielded fuel nozzle
US2701445A (en) * 1950-09-08 1955-02-08 Armstrong Siddeley Motors Ltd Ignition equipment for the combustion equipment of rocket motors
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter

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