GB1284341A - Fluid flow machine - Google Patents

Fluid flow machine

Info

Publication number
GB1284341A
GB1284341A GB4136/70A GB413670A GB1284341A GB 1284341 A GB1284341 A GB 1284341A GB 4136/70 A GB4136/70 A GB 4136/70A GB 413670 A GB413670 A GB 413670A GB 1284341 A GB1284341 A GB 1284341A
Authority
GB
United Kingdom
Prior art keywords
fan
duct
vane
wake
plane
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
GB4136/70A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB4136/70A priority Critical patent/GB1284341A/en
Priority to DE19712102804 priority patent/DE2102804A1/en
Priority to FR7102111A priority patent/FR2077376B1/fr
Publication of GB1284341A publication Critical patent/GB1284341A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F02K1/78—Other construction of jet pipes
    • 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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • 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
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1284341 Turbine, compressor and fan blade assemblies ROLLS ROYCE Ltd 28 Jan 1970 4136/70 Headings F1C, F1J and FIT A fluid-flow machine comprises an annular duct in which is mounted a ring of rotor blades there being at least one vane disposed downstream of the ring of rotor blades, the or each vane extending across the duct and being bent in a circumferential direction such that at least part of its leading edge lies in a plane which is substantially orthogonal to the plane containing the wake or wakes streaming in operation from one or more of the rotor blades whereby wake interaction between the blades and the or each vane is substantially reduced or eliminated. The invention is described with reference to a gas turbine ducted fan engine comprising fan rotor blades 15 and outlet guide vanes 17 located in a fan duct 16 defined between a fan casing 11 and the casing 12 of a gas turbine engine which drives the fan. The guide vanes 17 are bent outwardly in a circumferential direction opposite to the direction of rotation 20 of the fan blades 15. The radial limits of a "ribbon of wake" streaming from the trailing edge 22 of a fan rotor blade 15 are indicated at 30, Fig.3, and due to the circumferential bending of the guide vane 17 it can be seen that the plane of the "ribbon of wake" is substantially orthogonal to the plane in which the leading edge 24 of the guide vane lies. The object of the invention is to reduce noise level. Layers of sound absorbing material (35) may be disposed on the inner and outer walls of the fan duct, Fig.1 (not shown). The invention is applicable also to other machines such as a compressor duct or a turbine duct of a gas turbine engine.
GB4136/70A 1970-01-28 1970-01-28 Fluid flow machine Expired GB1284341A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB4136/70A GB1284341A (en) 1970-01-28 1970-01-28 Fluid flow machine
DE19712102804 DE2102804A1 (en) 1970-01-28 1971-01-21 Flow machine
FR7102111A FR2077376B1 (en) 1970-01-28 1971-01-22

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4136/70A GB1284341A (en) 1970-01-28 1970-01-28 Fluid flow machine

Publications (1)

Publication Number Publication Date
GB1284341A true GB1284341A (en) 1972-08-09

Family

ID=9771442

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4136/70A Expired GB1284341A (en) 1970-01-28 1970-01-28 Fluid flow machine

Country Status (3)

Country Link
DE (1) DE2102804A1 (en)
FR (1) FR2077376B1 (en)
GB (1) GB1284341A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
WO2008029062A2 (en) * 2006-09-07 2008-03-13 Airbus France Device for improving the effectiveness of acoustic treatments in an aircraft drive duct
CN110107532A (en) * 2019-05-22 2019-08-09 苏州顺福利智能科技有限公司 The improved flabellum of structure

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2505399A1 (en) * 1981-05-05 1982-11-12 Alsthom Atlantique DIRECT DRAWING FOR DIVERGENT VEINS OF STEAM TURBINE

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941781A (en) * 1955-10-13 1960-06-21 Westinghouse Electric Corp Guide vane array for turbines
FR1568944A (en) * 1968-02-29 1969-05-30
US3542152A (en) * 1968-04-08 1970-11-24 Gen Electric Sound suppression panel

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4131387A (en) * 1976-02-27 1978-12-26 General Electric Company Curved blade turbomachinery noise reduction
WO2008029062A2 (en) * 2006-09-07 2008-03-13 Airbus France Device for improving the effectiveness of acoustic treatments in an aircraft drive duct
FR2905734A1 (en) * 2006-09-07 2008-03-14 Airbus France Sas DEVICE FOR ENHANCING THE EFFICIENCY OF ACOUSTIC TREATMENTS IN A CONDUIT OF AN AIRCRAFT ENGINE
WO2008029062A3 (en) * 2006-09-07 2008-05-29 Airbus France Device for improving the effectiveness of acoustic treatments in an aircraft drive duct
JP2010502885A (en) * 2006-09-07 2010-01-28 エアバス フランス Device for improving the acoustic processing effect in ducts of aircraft power mechanisms.
US8167232B2 (en) 2006-09-07 2012-05-01 Airbus Operations Sas Device that makes it possible to improve the effectiveness of the acoustic treatments in a pipe of an aircraft power plant
CN101558224B (en) * 2006-09-07 2013-10-30 空中客车运营简化股份公司 Device for improving effectiveness of acoustic treatments in aircraft drive duct
CN110107532A (en) * 2019-05-22 2019-08-09 苏州顺福利智能科技有限公司 The improved flabellum of structure

Also Published As

Publication number Publication date
FR2077376A1 (en) 1971-10-22
DE2102804A1 (en) 1971-08-12
FR2077376B1 (en) 1975-01-17

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees