GB1096624A - Diffusers for fluid flows - Google Patents

Diffusers for fluid flows

Info

Publication number
GB1096624A
GB1096624A GB401964A GB401964A GB1096624A GB 1096624 A GB1096624 A GB 1096624A GB 401964 A GB401964 A GB 401964A GB 401964 A GB401964 A GB 401964A GB 1096624 A GB1096624 A GB 1096624A
Authority
GB
United Kingdom
Prior art keywords
flow
portions
passage
diffuser
oblique
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.)
Expired
Application number
GB401964A
Inventor
Stephen Downing Barnwell
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.)
Bristol Siddeley Engines Ltd
Original Assignee
Bristol Siddeley Engines Ltd
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 Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
Priority to GB401964A priority Critical patent/GB1096624A/en
Priority to FR3243A priority patent/FR1422633A/en
Publication of GB1096624A publication Critical patent/GB1096624A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,096,624. Boundary layer control. BRISTOL SIDDELEY ENGINES Ltd. Jan. 28, 1965 [Jan. 30, 1964], No. 4019/64. Heading F2R. [Also in Division F1] A diffuser for liquid or gaseous flow has a first passage part 10 diverging at an angle of 7 degrees, just below the maximum divergence for stable flow, discharging into a second passage part 11 of enlarged cross-section over a step 12. The profile of the edge of the step includes portions 12a oblique to the general direction 13 of fluid flow through the diffuser and converging downstream and portions 12b perpendicular to the flow. Such a profile reduces the rate of increase of cross-sectional area at the transition between passage parts 10 and 11, and the flow over the oblique portions 12a generates vortices 14 the axes of which extend in a downstream direction. These vortices re-energize the flow adjacent the passage walls by mixing the boundary layer flow back into the main stream and making the flow more uniform. In a modification, Fig. 3 (not shown), the second part of the diffuser passage is divergent at a rate greater than the maximum rate for stable flow and the oblique portions of the edge of the step are formed by plates (15) which are continuations of the walls of the passage part 10. In further modifications, the step edge consists entirely of oblique portions 12a, or the portions 12a may be asymmetrical so that vortices 14 of one hand predominate. The application of the diffuser to a gas-turbine engine combustion system is described (see Division F1).
GB401964A 1964-01-30 1964-01-30 Diffusers for fluid flows Expired GB1096624A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB401964A GB1096624A (en) 1964-01-30 1964-01-30 Diffusers for fluid flows
FR3243A FR1422633A (en) 1964-01-30 1965-01-26 Diffusers for fluid streams

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB401964A GB1096624A (en) 1964-01-30 1964-01-30 Diffusers for fluid flows

Publications (1)

Publication Number Publication Date
GB1096624A true GB1096624A (en) 1967-12-29

Family

ID=9769205

Family Applications (1)

Application Number Title Priority Date Filing Date
GB401964A Expired GB1096624A (en) 1964-01-30 1964-01-30 Diffusers for fluid flows

Country Status (2)

Country Link
FR (1) FR1422633A (en)
GB (1) GB1096624A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0619456A1 (en) * 1993-04-08 1994-10-12 ABB Management AG Fuel supply system for combustion chamber
EP0638732A1 (en) * 1993-08-03 1995-02-15 BDAG Balcke-Dürr Aktiengesellschaft Diffuser
DE19757187A1 (en) * 1997-12-22 1999-06-24 Abb Research Ltd Method and device for energy enrichment in a boundary layer adjacent to a flow-around surface
US6964698B1 (en) 2004-06-07 2005-11-15 Balcke-Durr Gmbh Gas supply for electrostatic filter and electrostatic filter arrangement
DE102007014226A1 (en) * 2007-03-24 2008-09-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Engine inlet flow homogenizing method for engine of airplane e.g. military aircraft, involves longitudinally dividing inlet flow of engine over intake cross-section into several branch flows

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4918926A (en) * 1982-05-20 1990-04-24 United Technologies Corporation Predfiffuser for a gas turbine engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0619456A1 (en) * 1993-04-08 1994-10-12 ABB Management AG Fuel supply system for combustion chamber
CH687832A5 (en) * 1993-04-08 1997-02-28 Asea Brown Boveri Fuel supply for combustion.
US5658358A (en) * 1993-04-08 1997-08-19 Abb Management Ag Fuel supply system for combustion chamber
EP0638732A1 (en) * 1993-08-03 1995-02-15 BDAG Balcke-Dürr Aktiengesellschaft Diffuser
DE19757187A1 (en) * 1997-12-22 1999-06-24 Abb Research Ltd Method and device for energy enrichment in a boundary layer adjacent to a flow-around surface
US6964698B1 (en) 2004-06-07 2005-11-15 Balcke-Durr Gmbh Gas supply for electrostatic filter and electrostatic filter arrangement
DE102007014226A1 (en) * 2007-03-24 2008-09-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Engine inlet flow homogenizing method for engine of airplane e.g. military aircraft, involves longitudinally dividing inlet flow of engine over intake cross-section into several branch flows
DE102007014226B4 (en) * 2007-03-24 2014-02-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Method and device for homogenizing an inlet flow into a fan-shaped inlet with a flat inlet cross-section

Also Published As

Publication number Publication date
FR1422633A (en) 1965-12-24

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