US3494539A - Fluid flow machine - Google Patents

Fluid flow machine Download PDF

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Publication number
US3494539A
US3494539A US712986A US3494539DA US3494539A US 3494539 A US3494539 A US 3494539A US 712986 A US712986 A US 712986A US 3494539D A US3494539D A US 3494539DA US 3494539 A US3494539 A US 3494539A
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fluid flow
blades
sleeve member
spaced apart
flow machine
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US712986A
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Frank Littleford
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Rolls Royce PLC
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Rolls Royce PLC
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    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades

Definitions

  • a fluid flow machine having a plurality of angularly spaced apart rotor blades carried by and extending radially outwardly of a sleeve member, an inner sleeve which is mounted within the sleeve member, the inner sleeve and sleeve member having inter-meshing parts to transmit drive therebetween, and a hub member which is mounted concentrically within the inner sleeve and which is connected thereto by a plurality of angularly spaced apart struts, the angular spacing between adjacent struts being substantially greater than that between adjacent blades means being provided to permit limited radial movement between the hub member and the sleeve member.
  • This invention concerns a fluid flow machine such, for example, as either a compressor or a turbine of a gas turbine engine, or a ducted fan driven thereby.
  • a fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular sleeve member, the rotor blades being carried by and extending radially outwardly thereof, a hub member mounted concentrically within the sleeve member, a plurality of angularly spaced apart struts which extend radially outwardly of the hub member, means to transmit drive between the struts and the sleeve member and means to permit limited radial movement between the hub member and the sleeve member.
  • a fluid flow machine having a plurality of angularly spaced apart rotor blades carried by and extending radially outwardly of an annular sleeve member, an inner annular sleeve which is mounted within the sleeve member, the inner sleeve and sleeve member having intermeshing parts to transmit drive therebetween, and a hub member which is mounted concentrically within the inner sleeve and which is connected thereto by a plurality of angularly spaced apart struts, the angular spacing between adjacent struts being substantially greater than that between adjacent blades means being provided to permit limited radial movement between the hub member and the sleeve member.
  • the struts are open to the fluid flow but are so shaped as to have substantially no ellect upon the energy imparted to or taken from the fluid flowing through the machine.
  • the said blades are preferably so shaped as to have a substantially constant effect from their roots to their 7 maximum efliciency could not, however, be achieved 1f the said overcrowding were allowed to occur.
  • the angular spacing between adjacent struts is preferably at least twice as great as that between adjacent blades.
  • a plurality of angularly spaced apart sectors of the inner sleeve and of the sleeve member may be provided with intermeshing teeth.
  • the inner sleeve and sleeve member may be radially spaced apart to permit said limited radial movement therebetween.
  • the sleeve member may be formed of fibre-reinforced or other material having angularly spaced apart sector-shaped inserts therein which are provided with the said teeth.
  • the said blades preferably effect compression of the said fluid.
  • the said blades may be those of a ducted fan mounted about and driven by a gas turbine engine.
  • FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine provided with a front ducted fan in accordance with the present invention
  • FIGURE 2 is a broken-away sectional view on a larger scale of part of the structure shown in FIGURE 1,
  • FIGURE 3 is a broken-away front elevation looking in the direction of the arrow 3 of FIGURE 1, and
  • FIGURE 4 is a broken-away section taken on the line 4-4 of FIGURE 2.
  • FIGURE 1 there is shown a power plant for the forward propulsion of an aircraft comprising a gas turbine engine 10 having an engine casing 11 within which there are mounted in flow series, inlet guide vanes 12, one or more compressors 13 (FIGURE 2), combustion equipment (not shown) and one or more turbines (not shown).
  • a gas turbine engine 10 having an engine casing 11 within which there are mounted in flow series, inlet guide vanes 12, one or more compressors 13 (FIGURE 2), combustion equipment (not shown) and one or more turbines (not shown).
  • a fan casing 14 Mounted concentrically about the front portion of the engine casing 11 is a fan casing 14 within which are mounted a plurality of angularly spaced apart rotor blades 15 of a ducted front fan.
  • the rotor blades 15 which may, if desired, be formed of an epoxy or other synthetic resin, are carried by and extend radially outwardly of a sleeve member 16.
  • the sleeve member 16 is formed of compacted fibrereinforced material.
  • the fibres may be carboniferous, boron, or glass fibres coated with an epoxy orother synthetic resin or, alternatively, coated with a metal or alloy, e.g. with a nickel-chronmium alloy.
  • the sleeve member 16 has a plurality (e.g. three or four) of angularly spaced apart sector-shaped inserts 20 embedded therein.
  • the inserts 20 are provided with teeth 21 (FIGURE 4) which mesh with teeth 22, the teeth 22 being provided at a plurality of correspondingly angularly spaced apart sectors of an inner sleeve 23 which is mounted within the sleeve member 16. Except in the said sectors, the inner sleeve 23 and the sleeve member 16 are radially spaced apart so as to permit limited radial movement therebetween.
  • the inner sleeve 23 is connected to the radially outer ends of a plurality of angularly spaced apart aluminum or other struts 24 which extend radially outwardly from a hub member 25, the latter being mounted concentrically within the sleeve member 16 and inner sleeve 23.
  • the angular spacing between adjacent struts 24 is very much greater than that between adjacent blades 15 and may, as shown, he more than twice as great. The effect of this is that the overcrowding of the blades 15 at the hub 25 which could otherwise occur, if the blades extended to the latter, is avoided.
  • this enables the blades 15 to be shaped 0 as shown in FIGURES 3 and 4 so that, from their roots to their tips, they effect substantially constant work on the air passing through the ducted fan and compressed thereby.
  • the hub member 25 may be driven by way of a coupling 26 (e.g. that sold under the registered trademark Curvic) from a shaft 27 which is driven by the turbine (not shown) of the engine.
  • This drive is transmitted to the rotor blades by way of the struts 24 and the teeth 21, 22 limited radial movement thus being possible between the hub member and the sleeve member 16. This limited radial movement will compensate for some differential thermal expansion.
  • a fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular outer sleeve mem ber, said rotor blades being carried by and extending radially outwardly from said outer sleeve, an inner annular sleeve member which is mounted within said outer sleeve member, said inner sleeve and said outer sleeve members having intermeshing parts along at least portions of their respective outer and inner surfaces to transmit drive therebetween, a hub member which is mounted concentrically within said inner sleeve, a plurality of angularly spaced apart struts which connect said hub member to said inner sleeve, the angular spacing between adjacent ones of said struts being substantially greater than the spacing between adjacent ones of said blades and means provided to permit limited radial movement between said hub member and said sleeve member.
  • a fluid flow machine as claimed in claim 1 in which the struts are exposed to the fluid flowing through the machine but are shaped to have substantially zero effect upon the energy exchanged with the fluid.
  • a fluid flow machine as claimed in claim 1 in which the said blades are shaped to have a substantially constant effect from their roots to their tips upon the energy which they exchange with the fluid flowing through the machine.
  • a fluid flow machine as claimed in claim 1 in which the angular spacing between adjacent ones of said struts is at least twice as great as that between adjacent ones of said blades.
  • a fluid flow machine as claimed in claim 1 in which the inner sleeve and the outer sleeve member each have a plurality of angularly spaced apart sectors on the respective outer and inner surfaces thereof upon which are mounted said intermeshing teeth.
  • a fluid flow machine as claimed in claim 5 in which, except for the intermeshing of said teeth on said sectors, the inner sleeve and the outer sleeve member are radially spaced apart to permit limited radial movement therebetween.
  • a fluid flow machine as claimed in claim 6 in which the outer sleeve member is formed of fibre-reinforced material having angularly spaced apart sector-shaped inserts therein which are provided with the said teeth.
  • a fluid flow machine as claimed in claim 8 in which the said blades are those of a ducted fan, and having in addition a gas turbine engine mounted within the fan and driving said fan.
  • a fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular sleeve member, said rotor blades being carried by and extending radially outwardly from said annular sleeve member, a hub member mounted concentrically within said annular sleeve member, a plurality of angularly spaced apart struts which extend radially outwardly from said hub member, means for transmitting rotational energy between said struts and said annular sleeve member and means to permit limited radial movement between said hub member and said sleeve member.

Description

Feb. 10, 1970 F. LITTLEFORD 3,494,539
FLUID FLOW MACHINE 7 Filed March 14, 1968 2 Sheets-Sheet 1' A tlorneys Feb. 10, 1970 F. LITTLEFORD 3,494,539
FLUID FLOW MACHINE I Filed March 14, 1968 2 Sheets-Skieet a A tlorneys United States Patent Int. Cl. B63h1/04; F04d 19/02 U.S. Cl. 230--116 Claims ABSTRACT OF THE DISCLOSURE A fluid flow machine having a plurality of angularly spaced apart rotor blades carried by and extending radially outwardly of a sleeve member, an inner sleeve which is mounted within the sleeve member, the inner sleeve and sleeve member having inter-meshing parts to transmit drive therebetween, and a hub member which is mounted concentrically within the inner sleeve and which is connected thereto by a plurality of angularly spaced apart struts, the angular spacing between adjacent struts being substantially greater than that between adjacent blades means being provided to permit limited radial movement between the hub member and the sleeve member.
This invention concerns a fluid flow machine such, for example, as either a compressor or a turbine of a gas turbine engine, or a ducted fan driven thereby. According to one aspect of the present invention, there is provided a fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular sleeve member, the rotor blades being carried by and extending radially outwardly thereof, a hub member mounted concentrically within the sleeve member, a plurality of angularly spaced apart struts which extend radially outwardly of the hub member, means to transmit drive between the struts and the sleeve member and means to permit limited radial movement between the hub member and the sleeve member.
In another aspect of the present invention, there is provided a fluid flow machine having a plurality of angularly spaced apart rotor blades carried by and extending radially outwardly of an annular sleeve member, an inner annular sleeve which is mounted within the sleeve member, the inner sleeve and sleeve member having intermeshing parts to transmit drive therebetween, and a hub member which is mounted concentrically within the inner sleeve and which is connected thereto by a plurality of angularly spaced apart struts, the angular spacing between adjacent struts being substantially greater than that between adjacent blades means being provided to permit limited radial movement between the hub member and the sleeve member.
As will be appreciated, in a fluid flow machine in accordance with the present invention overcrowding of the blades at the hub member is avoided.
Preferably the struts are open to the fluid flow but are so shaped as to have substantially no ellect upon the energy imparted to or taken from the fluid flowing through the machine.
The said blades are preferably so shaped as to have a substantially constant effect from their roots to their 7 maximum efliciency could not, however, be achieved 1f the said overcrowding were allowed to occur.
3,494,539 Patented Feb. 10, 1970 The angular spacing between adjacent struts is preferably at least twice as great as that between adjacent blades.
A plurality of angularly spaced apart sectors of the inner sleeve and of the sleeve member may be provided with intermeshing teeth.
Except in the said sectors, the inner sleeve and sleeve member may be radially spaced apart to permit said limited radial movement therebetween.
Thus the sleeve member may be formed of fibre-reinforced or other material having angularly spaced apart sector-shaped inserts therein which are provided with the said teeth.
The said blades preferably effect compression of the said fluid. Thus the said blades may be those of a ducted fan mounted about and driven by a gas turbine engine.
The invention is illustrated, merely by way of example, in the accompanying drawings, in which:
FIGURE 1 is a diagrammatic view, partly in section, of a gas turbine engine provided with a front ducted fan in accordance with the present invention,
FIGURE 2 is a broken-away sectional view on a larger scale of part of the structure shown in FIGURE 1,
FIGURE 3 is a broken-away front elevation looking in the direction of the arrow 3 of FIGURE 1, and
FIGURE 4 is a broken-away section taken on the line 4-4 of FIGURE 2.
In FIGURE 1 there is shown a power plant for the forward propulsion of an aircraft comprising a gas turbine engine 10 having an engine casing 11 within which there are mounted in flow series, inlet guide vanes 12, one or more compressors 13 (FIGURE 2), combustion equipment (not shown) and one or more turbines (not shown).
Mounted concentrically about the front portion of the engine casing 11 is a fan casing 14 within which are mounted a plurality of angularly spaced apart rotor blades 15 of a ducted front fan. The rotor blades 15 which may, if desired, be formed of an epoxy or other synthetic resin, are carried by and extend radially outwardly of a sleeve member 16.
The sleeve member 16 is formed of compacted fibrereinforced material. Thus, the fibres may be carboniferous, boron, or glass fibres coated with an epoxy orother synthetic resin or, alternatively, coated with a metal or alloy, e.g. with a nickel-chronmium alloy.
The sleeve member 16 has a plurality (e.g. three or four) of angularly spaced apart sector-shaped inserts 20 embedded therein. The inserts 20 are provided with teeth 21 (FIGURE 4) which mesh with teeth 22, the teeth 22 being provided at a plurality of correspondingly angularly spaced apart sectors of an inner sleeve 23 which is mounted within the sleeve member 16. Except in the said sectors, the inner sleeve 23 and the sleeve member 16 are radially spaced apart so as to permit limited radial movement therebetween.
The inner sleeve 23 is connected to the radially outer ends of a plurality of angularly spaced apart aluminum or other struts 24 which extend radially outwardly from a hub member 25, the latter being mounted concentrically within the sleeve member 16 and inner sleeve 23. As will be seen from FIGURES 3 and 4, the angular spacing between adjacent struts 24 is very much greater than that between adjacent blades 15 and may, as shown, he more than twice as great. The effect of this is that the overcrowding of the blades 15 at the hub 25 which could otherwise occur, if the blades extended to the latter, is avoided. Moreover, this enables the blades 15 to be shaped 0 as shown in FIGURES 3 and 4 so that, from their roots to their tips, they effect substantially constant work on the air passing through the ducted fan and compressed thereby.
Such constant work blades are desirable to maximise the efficiency of the ducted fan.
If, however, in contrast to this, overcrowding of the blades at the hub member were permitted, then although constant work blades could be provided, the work produced thereby would be very small because it could not be greater than the maximum amount of Work produced at the root of the blade and the latter amount is limited by the speed of the blade, which is at a minimum at the root. In the case of the present invention, however, the blade roots are at some distance from the hub and therefore move with greater velocity.
The struts 24, on the other hand, although open to the air passing through the gas turbine engine, are so shaped as to do substantially no work on this air.
As shown in FIGURE 2, the hub member 25 may be driven by way of a coupling 26 (e.g. that sold under the registered trademark Curvic) from a shaft 27 which is driven by the turbine (not shown) of the engine. This drive is transmitted to the rotor blades by way of the struts 24 and the teeth 21, 22 limited radial movement thus being possible between the hub member and the sleeve member 16. This limited radial movement will compensate for some differential thermal expansion.
We claim:
1. A fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular outer sleeve mem ber, said rotor blades being carried by and extending radially outwardly from said outer sleeve, an inner annular sleeve member which is mounted within said outer sleeve member, said inner sleeve and said outer sleeve members having intermeshing parts along at least portions of their respective outer and inner surfaces to transmit drive therebetween, a hub member which is mounted concentrically within said inner sleeve, a plurality of angularly spaced apart struts which connect said hub member to said inner sleeve, the angular spacing between adjacent ones of said struts being substantially greater than the spacing between adjacent ones of said blades and means provided to permit limited radial movement between said hub member and said sleeve member.
2. A fluid flow machine as claimed in claim 1 in which the struts are exposed to the fluid flowing through the machine but are shaped to have substantially zero effect upon the energy exchanged with the fluid.
3. A fluid flow machine as claimed in claim 1 in which the said blades are shaped to have a substantially constant effect from their roots to their tips upon the energy which they exchange with the fluid flowing through the machine.
4. A fluid flow machine as claimed in claim 1 in which the angular spacing between adjacent ones of said struts is at least twice as great as that between adjacent ones of said blades.
5. A fluid flow machine as claimed in claim 1 in which the inner sleeve and the outer sleeve member each have a plurality of angularly spaced apart sectors on the respective outer and inner surfaces thereof upon which are mounted said intermeshing teeth.
6. A fluid flow machine as claimed in claim 5 in which, except for the intermeshing of said teeth on said sectors, the inner sleeve and the outer sleeve member are radially spaced apart to permit limited radial movement therebetween.
7. A fluid flow machine as claimed in claim 6 in which the outer sleeve member is formed of fibre-reinforced material having angularly spaced apart sector-shaped inserts therein which are provided with the said teeth.
8. A fluid flow machine as claimed in claim 1 in which the said blades comprise means to effect compression of the said fluid.
9. A fluid flow machine as claimed in claim 8 in which the said blades are those of a ducted fan, and having in addition a gas turbine engine mounted within the fan and driving said fan.
10. A fluid flow machine having a plurality of angularly spaced apart rotor blades, an annular sleeve member, said rotor blades being carried by and extending radially outwardly from said annular sleeve member, a hub member mounted concentrically within said annular sleeve member, a plurality of angularly spaced apart struts which extend radially outwardly from said hub member, means for transmitting rotational energy between said struts and said annular sleeve member and means to permit limited radial movement between said hub member and said sleeve member.
References Cited UNITED STATES PATENTS 3,037,742 6/ 1962 Dent et a1. 3,070,284 12/1962 Kent. 3,216,654 11/1965 Kappus.
FOREIGN PATENTS 981,476 1/ 1965 Great Britain. 1,003,313 9/1965 Great Britain.
-EVERETTE A. POWELL, JR., Primary Examiner US. Cl. X.R.
US712986A 1967-04-03 1968-03-14 Fluid flow machine Expired - Lifetime US3494539A (en)

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Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3905722A (en) * 1972-03-15 1975-09-16 Rolls Royce 1971 Ltd Fluid flow machines
US4012165A (en) * 1975-12-08 1977-03-15 United Technologies Corporation Fan structure
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
DE3719717A1 (en) * 1986-07-02 1988-01-14 Rolls Royce Plc TURBINE
US4767271A (en) * 1986-07-02 1988-08-30 Rolls-Royce Plc Gas turbine engine power turbine
US4969326A (en) * 1988-08-15 1990-11-13 General Electric Company Hoop shroud for the low pressure stage of a compressor
US5224341A (en) * 1992-01-06 1993-07-06 United Technologies Corporation Separable fan strut for a gas turbofan powerplant
US5358382A (en) * 1993-07-21 1994-10-25 Eaton Corporation Fan and fan drive assembly
US5649419A (en) * 1995-01-27 1997-07-22 The Boeing Company Rotating acoustically lined inlet splitter for a turbo-fan engine
US20050155342A1 (en) * 2004-01-21 2005-07-21 Pauley Gerald A. Methods and apparatus for assembling gas turbine engines
GB2455785A (en) * 2007-12-21 2009-06-24 Rolls Royce Plc An annular non-metallic component comprising a bore with a sleeve
US8667775B1 (en) * 2009-08-05 2014-03-11 The Boeing Company Reverse flow engine core having a ducted fan with integrated secondary flow blades
US8813864B2 (en) 2011-09-09 2014-08-26 Jack D. Layton Support system for a box blade attached to a tractor
US20180291929A1 (en) * 2017-04-10 2018-10-11 Rolls-Royce Plc Acoustic attenuation in gas turbine engines
US20220194619A1 (en) * 2018-07-13 2022-06-23 Textron Innovations Inc. Fan clutch for convertible engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20160070079A (en) * 2013-10-03 2016-06-17 프랑코 토시 메카니카 에세.피.아. Rotor stage of axial turbine with improved chord/pitch ratio

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US3037742A (en) * 1959-09-17 1962-06-05 Gen Motors Corp Compressor turbine
US3070284A (en) * 1960-10-07 1962-12-25 Gen Electric Turbo-fan rotor
GB981476A (en) * 1963-11-04 1965-01-27 Rolls Royce Gas turbine engine vane assembly
GB1003313A (en) * 1960-11-17 1965-09-02 Bristol Siddeley Engines Ltd Improvements in blades for ducted axial flow machines
US3216654A (en) * 1965-11-09 Tureeofan engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3216654A (en) * 1965-11-09 Tureeofan engine
US3037742A (en) * 1959-09-17 1962-06-05 Gen Motors Corp Compressor turbine
US3070284A (en) * 1960-10-07 1962-12-25 Gen Electric Turbo-fan rotor
GB1003313A (en) * 1960-11-17 1965-09-02 Bristol Siddeley Engines Ltd Improvements in blades for ducted axial flow machines
GB981476A (en) * 1963-11-04 1965-01-27 Rolls Royce Gas turbine engine vane assembly

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3905722A (en) * 1972-03-15 1975-09-16 Rolls Royce 1971 Ltd Fluid flow machines
US4063847A (en) * 1974-08-23 1977-12-20 Rolls-Royce (1971) Limited Gas turbine engine casing
US4012165A (en) * 1975-12-08 1977-03-15 United Technologies Corporation Fan structure
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
DE3719717A1 (en) * 1986-07-02 1988-01-14 Rolls Royce Plc TURBINE
US4767271A (en) * 1986-07-02 1988-08-30 Rolls-Royce Plc Gas turbine engine power turbine
US4826403A (en) * 1986-07-02 1989-05-02 Rolls-Royce Plc Turbine
US4969326A (en) * 1988-08-15 1990-11-13 General Electric Company Hoop shroud for the low pressure stage of a compressor
US5471743A (en) * 1992-01-06 1995-12-05 United Technologies Corporation Method of disassembling a gas turbine engine power plant
US5224341A (en) * 1992-01-06 1993-07-06 United Technologies Corporation Separable fan strut for a gas turbofan powerplant
US5358382A (en) * 1993-07-21 1994-10-25 Eaton Corporation Fan and fan drive assembly
US5649419A (en) * 1995-01-27 1997-07-22 The Boeing Company Rotating acoustically lined inlet splitter for a turbo-fan engine
US20050155342A1 (en) * 2004-01-21 2005-07-21 Pauley Gerald A. Methods and apparatus for assembling gas turbine engines
US7094033B2 (en) * 2004-01-21 2006-08-22 General Electric Company Methods and apparatus for assembling gas turbine engines
GB2455785A (en) * 2007-12-21 2009-06-24 Rolls Royce Plc An annular non-metallic component comprising a bore with a sleeve
GB2455785B (en) * 2007-12-21 2009-11-11 Rolls Royce Plc Annular component
US8667775B1 (en) * 2009-08-05 2014-03-11 The Boeing Company Reverse flow engine core having a ducted fan with integrated secondary flow blades
US8813864B2 (en) 2011-09-09 2014-08-26 Jack D. Layton Support system for a box blade attached to a tractor
US20180291929A1 (en) * 2017-04-10 2018-10-11 Rolls-Royce Plc Acoustic attenuation in gas turbine engines
US20220194619A1 (en) * 2018-07-13 2022-06-23 Textron Innovations Inc. Fan clutch for convertible engine
US11939077B2 (en) * 2018-07-13 2024-03-26 Textron Innovations Inc. Fan clutch for convertible engine

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DE1751094A1 (en) 1970-08-13
GB1118898A (en) 1968-07-03
FR1556914A (en) 1969-02-07

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