GB1259124A – – Google Patents
GB1259124A – – Google Patents
Info
Publication number
GB1259124A
GB1259124A
GB5817868A
GB1259124DA
GB1259124A
GB 1259124 A
GB1259124 A
GB 1259124A
GB 5817868 A
GB5817868 A
GB 5817868A
GB 1259124D A
GB1259124D A
GB 1259124DA
GB 1259124 A
GB1259124 A
GB 1259124A
Authority
GB
United Kingdom
Prior art keywords
restrictor
duct
annular
disposed
flame tube
Prior art date
1968-12-06
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.)
Expired
Application number
GB5817868A
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.)
1968-12-06
Filing date
1968-12-06
Publication date
1972-01-05
1968-12-06
Application filed
filed
Critical
1972-01-05
Publication of GB1259124A
publication
Critical
patent/GB1259124A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
Classifications
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
F15D1/00—Influencing flow of fluids
F15D1/02—Influencing flow of fluids in pipes or conduits
F15D1/06—Influencing flow of fluids in pipes or conduits by influencing the boundary layer
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
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
F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
F23R3/26—Controlling the air flow
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
Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T137/00—Fluid handling
Y10T137/206—Flow affected by fluid contact, energy field or coanda effect [e.g., pure fluid device or system]
Y10T137/2273—Device including linearly-aligned power stream emitter and power stream collector
Abstract
1,259,124. Boundary layer control. DEFENCE SECRETARY OF STATE FOR. 27 Nov., 1969 [6 Dec., 1968], No. 58178/68. Heading F2R. [Also in Division F1] The invention relates to combustion apparatus including a flow control device comprising a duct, a flow restrictor within the duct and having a throat and a divergent portion downstream of the throat, there being means for applying motion to a surface of the flow restrictor so as to control the boundary layer within the restrictor. In Fig. 1 a restrictor in the form of a Venturi device 2 is disposed within a tubular duct 1 through which fluid flows as indicated by arrows A to a combustion chamber (nob shown). Openings 5 are formed in the wall of the divergent part of the restrictor and suction is applied through the openings 5, space 3 and duct 4 as indicated by arrow B thus preventing flow separation at the divergent wall. Such flow separation is indicated at the lower part of the Figure. The invention is described with reference to its application to combustion equipment of a gas turbine engine, the equipment comprising an outer air casing 6 and an inner flame tube 7, a restrictor 2 being mounted in the primary air inlet duct 1 of the flame tube, openings 5 being provided in the divergent wall of the restrictor as in Fig. 1. A fuel injector 11 and swirl vanes 10 are mounted in the duct 1 downstream of the restrictor. In Fig. 4 (not shown), a baffle 12 is disposed around the fuel injector leaving an annular opening for passage of air. In Fig. 7 the combustion equipment is of the annular type comprising an annular flame tube 32, 33 disposed within an annular air casing 30, 31. An annular restriction formed by ring members 35, 36 is disposed at the inlet of the flame tube, the members 35, 36 being formed with openings 37, 38 for the application of suction through lines 41, 42. A baffle 43 is disposed downstream of the restriction. In Fig. 6 the invention is shown applied to a fuel vaporizing tube 1 of J-shape, the vaporizing tube being mounted in the wall 20 of a flame tube.
GB5817868A
1968-12-06
1968-12-06
Expired
GB1259124A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB5817868
1968-12-06
Publications (1)
Publication Number
Publication Date
GB1259124A
true
GB1259124A
(en)
1972-01-05
Family
ID=10480953
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB5817868A
Expired
GB1259124A
(en)
1968-12-06
1968-12-06
Country Status (4)
Country
Link
US
(1)
US3643431A
(en)
DE
(1)
DE1960971A1
(en)
FR
(1)
FR2027582A1
(en)
GB
(1)
GB1259124A
(en)
Cited By (1)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2168143A
(en)
*
1984-12-08
1986-06-11
Messerschmitt Boelkow Blohm
A regulable diffuser for an air intake on an aircraft
Families Citing this family (24)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3737281A
(en)
*
1971-09-27
1973-06-05
C Guth
Fuel mixing shroud for heating torches
US3851466A
(en)
*
1973-04-12
1974-12-03
Gen Motors Corp
Combustion apparatus
GB1573926A
(en)
*
1976-03-24
1980-08-28
Rolls Royce
Fluid flow diffuser
US4041984A
(en)
*
1976-07-01
1977-08-16
General Motors Corporation
Jet-driven helmholtz fluid oscillator
US4106136A
(en)
*
1977-05-23
1978-08-15
Lippincott Sr Richard L
Toilet flush flow accelerator
FR2401311A1
(en)
*
1977-08-25
1979-03-23
Europ Turb Vapeur
EXHAUST SYSTEM FOR AXIAL CONDENSABLE FLUID TURBINE
DE2810444C2
(en)
*
1978-03-10
1985-01-17
Kraftwerk Union AG, 4330 Mülheim
Slit-shaped guide apparatus for guiding gaseous flows during the separation of isotope mixtures under selective laser excitation
US4231971A
(en)
*
1979-04-11
1980-11-04
Dresser Industries, Inc.
Flow method and device
DE3436151A1
(en)
*
1983-10-18
1985-05-02
Dirk Alexander 5840 Schwerte Brügmann
Support for price rails or the like
US5749217A
(en)
*
1991-12-26
1998-05-12
Caterpillar Inc.
Low emission combustion system for a gas turbine engine
GB9726697D0
(en)
*
1997-12-18
1998-02-18
Secr Defence
Fuel injector
CA2380474A1
(en)
1999-07-29
2001-02-08
Siemens Aktiengesellschaft
Appliance and method for controlling a gas turbine cooling air flow, and a gas turbine through which cooling air flows
US6775983B2
(en)
*
2002-05-21
2004-08-17
General Electric Company
Flow control device for a combustor
US7007478B2
(en)
*
2004-06-30
2006-03-07
General Electric Company
Multi-venturi tube fuel injector for a gas turbine combustor
US7003958B2
(en)
*
2004-06-30
2006-02-28
General Electric Company
Multi-sided diffuser for a venturi in a fuel injector for a gas turbine
US6983600B1
(en)
*
2004-06-30
2006-01-10
General Electric Company
Multi-venturi tube fuel injector for gas turbine combustors
US7093438B2
(en)
*
2005-01-17
2006-08-22
General Electric Company
Multiple venture tube gas fuel injector for a combustor
US7389643B2
(en)
*
2005-01-31
2008-06-24
General Electric Company
Inboard radial dump venturi for combustion chamber of a gas turbine
DE102006041955A1
(en)
*
2006-08-30
2008-03-20
Deutsches Zentrum für Luft- und Raumfahrt e.V.
Method for controlling combustion in a combustion chamber and combustion chamber device
US8919185B2
(en)
*
2009-12-14
2014-12-30
Schlumberger Technology Corporation
System and method for swirl generation
EP3341615B1
(en)
*
2015-08-28
2021-09-29
Dayco IP Holdings, LLC
Restrictors using the venturi effect
GB201808070D0
(en)
*
2018-05-18
2018-07-04
Rolls Royce Plc
Burner
FR3091574B1
(en)
*
2019-01-08
2020-12-11
Safran Aircraft Engines
TURBOMACHINE INJECTION SYSTEM, INCLUDING A MIXER BOWL AND SWIRL HOLES
CN109915857B
(en)
*
2019-02-28
2021-01-15
西北工业大学
Novel combustion chamber head
Family Cites Families (8)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3123285A
(en)
*
1964-03-03
Diffuser with boundary layer control
US2656096A
(en)
*
1946-01-04
1953-10-20
Rateau Soc
Centrifugal pump and compressor
GB738006A
(en)
*
1952-07-12
1955-10-05
Rolls Royce
Improvements in or relating to gas turbine engines
US2788719A
(en)
*
1954-02-11
1957-04-16
Klmberly Clark Corp
Flow control apparatus
FR1117244A
(en)
*
1954-12-20
1956-05-18
Snecma
Supersonic wind tunnel with variable number of machines
US2841182A
(en)
*
1955-12-29
1958-07-01
Westinghouse Electric Corp
Boundary layer fluid control apparatus
US3216455A
(en)
*
1961-12-05
1965-11-09
Gen Electric
High performance fluidynamic component
GB1184683A
(en)
*
1967-08-10
1970-03-18
Mini Of Technology
Improvements in or relating to Combustion Apparatus.
1968
1968-12-06
GB
GB5817868A
patent/GB1259124A/en
not_active
Expired
1969
1969-12-04
DE
DE19691960971
patent/DE1960971A1/en
active
Pending
1969-12-04
US
US882152A
patent/US3643431A/en
not_active
Expired – Lifetime
1969-12-05
FR
FR6942224A
patent/FR2027582A1/fr
not_active
Withdrawn
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2168143A
(en)
*
1984-12-08
1986-06-11
Messerschmitt Boelkow Blohm
A regulable diffuser for an air intake on an aircraft
GB2168143B
(en)
*
1984-12-08
1989-06-14
Messerschmitt Boelkow Blohm
A regulable diffuser for an air intake on an aircraft
Also Published As
Publication number
Publication date
DE1960971A1
(en)
1970-06-25
FR2027582A1
(en)
1970-10-02
US3643431A
(en)
1972-02-22
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Legal Events
Date
Code
Title
Description
1972-05-17
PS
Patent sealed [section 19, patents act 1949]
1983-06-29
PCNP
Patent ceased through non-payment of renewal fee
