Gas turbine engines and bladed rotors therefor
0 United States Patent 1 1 1 1 3,876,333 Ronson Apr. 8, 1975 I5 l GAS TURBINE ENGINES AND BLADED 3.528.752 9/1970 Davies et al. 416/157 ROTORS THEREFOR 3.664 763 S/I972 Chilman I l s w 415/129 3.794.440 2/l974 McMurtry t. 4l5/I57 [75] Inventor: George Lancaster Ronson,  
  Chehenham England FOREIGN PATENTS OR APPLICATIONS Assigneez Dowlry Rom] Limited, Gloucester, l,256.667 2/!961 France 4l6/l57 E I d I an Primary E.\&#39;aminerl-lenry F. Raduazo [22] F1led: Feb. 15, 1974 Attorney, Agent, or FirmYoung &amp; Thompson [2!] Appl. No.: 443,143  
  [57] ABSTRACT [30] Foreign Application Priority Data Cl fi d t 29%;&#34;? t i bl f b &#34;1h ac roorw1c1sroaae1na y-pass uc. e I973 Ummd Kingdom 7886/73 rotor includes a hub which carries, so as to be rotatable therewith, a liquid reservoir at least one pump 415/ operable upon rotation of the rotor, relief alve means (58&#39; Fieid 56 745 associated with the pump and an actuator for adjust- HS/129 ing the blades of the rotor to vary flow of fluid over the blades. The pump, when operating, draws liquid from the reservoir and delivers it under pressure to {56] References Cited said actuator. Liquid discharged by the relief valve UNITED STATES PATENTS means in flowing to the reservoir passes adjacent to an 3.420Jll l/I969 Davies et al. v. 416/245 outer wall of the hub, 3,476,486 ll/l969 Davies et al. 4l6/I57 3.4s7,1 x11 1 1970 Davies et al. 416/157 9 Clalms. 5 Drawmg Flgures I V d 2 3 GAS TURBINE ENGINES AND BLADED ROTORS THEREFOR This invention relates to gas turbine engines, more particularly gas turbine engines of the by-pass type, and to bladed rotors therefor.  
  According to the invention a gas turbine engine of the bypass type includes a bladed rotor which is rotatable in a by-pass duct, said rotor including a hub which carries, so as to be rotatable therewith, a liquid reservoir, at least one pump operable upon rotation of the rotor, relief valve means associated with said pump, and an actuator for adjusting the blades of the rotor to vary flow of fluid over the blades, said pump, when op erating, drawing liquid from the reservoir and delivering it under pressure to said actuator, and liquid discharged by the relief valve means in flowing to the reservoir passing adjacent to an outer wall of the hub.  
  Also according to the invention there is provided a bladed rotor, suitable for a gas turbine engine of the bypass type, including a hub which carries, so as to be rotatable therewith, a liquid reservoir, at least one pump operable upon rotation of the rotor, relief valve means associated with said pump, and an actuator for adjusting the blades of the rotor to vary flow of fluid over the blades, said pump, when operating, drawing liquid from the reservoir and delivering it under pressure to said actuator, and liquid discharged by the relief valve means in flowing to the reservoir passing adjacent to an outer wall of the hub.  
  The flow from said relief valve means to the reservoir may be by way of means defining a spiral channel.  
  Means may be provided externally of said hub whereby air is brought into heat-exchange relation, by way of said outer wall of the hub, with the liquid pass ing along said spiral channel. These means may comprise ducting which incorporates impeller blading formed as part of spinner structure, said spinner struc ture being attachable to the hub for rotation therewith.  
  The relief valve means may comprise a respective relief valve disposed in the casing of said pump.  
  Mechanical means may connect said pump with nonrotative structure external of the rotor to afford its operation upon rotation of the rotor. The mechanical means may include gearing, also carried by the hub, and shafting coaxial with the hub and extending from the gearing to said non-rotative structure.  
  The actuator may be of vane-type having its axis of rotation coincident with the rotational axis of the rotor.  
  One embodiment ofthe invention will now be particularly described, by way of example with reference to the accompanying drawings, of which,  
  FIG. I is a partial cross-sectional diagrammatic side elevation of a gas turbine engine of the by-pass type having a ducted-fan,  
  FIG. 2, comprising upper part A and lower part B, is an enlarged cross-section of the hub of the fan shown in FIG. 1,  
  FIG. 3 is a diagrammatic cross-section taken along the line Ill III on FIG. 2, and,  
 FIG. 4 is an enlarged view of a portion of FIG. 2A.  
  Referring to the drawings, an aircraft gas turbine engine 1 comprises a compressor 2, a combustion section 3 and a turbine section 4. A splined output shaft 5 of the engine carries a fan 6, which is rotatable within a by-pass duct 7, itself mounted upon the casing of the compressor 2 by means of stator blades 8. The fan thus charges both the by-pass duct 7 and the inlet 9 of the compressor 2.  
  The fan 6 comprises a bladed rotor having 14 blades 12, each mounted as shown in FIG. 2 in bearings 13 and 14 in respective sockets 15 carried by a hub 16. The blades are variable in pitch about their longitudinal pitch-change axes l7 and each is connected by means of a splined member 18 to a respective bevel gear 19 within the hub 16.  
  The hub 16 is generally of annular form having a splined central opening 20 which incorporates a pair of cone mountings 21, 22 by which the rotor is adapted for ready fitment to the output shaft 5. A screw threaded ring member 24 retains the rotor in the axial sense on the shaft 5.  
  Pitch-variation ofthe blades is effected by the operation of a servo mechanism which includes a pitchchange actuator 25, for example of the hydraulically operable balanced-vane-type, which is rotatable with the rotor 6 and which has its axis of rotation coincident with the axis 26 of rotation of the rotor.  
  The actuator 25 which is of annular form and enclosed within the hub 16 has a multiplicity of chambers. in this embodiment twelve, formed by a first multivaned assembly or actuator part 27 and a second multivaned assembly or actuator part 28.  
  The parts 27 and 28 are both capable of angular movement with respect to the hub 16 about the axis 26, and are movable in opposite directions, the one with respect to the other. The outer wall of the actuator is formed with a radially outwardly directed flange 29. The part 27 has a rearwardly extending member 30 bolted thereto which is formed with a ring of bevel gear teeth 31 which is in engagement with all of the blade bevel gears 19.  
  The part 28 has a rearwardly extending portion 32 of externally splined tubular form upon which is mounted an internally splined stepped tubular member 33 which, at its rearward end portion, is provided with a ring 34 of bevel gear teeth. The ring 34 engages all of the blade bevel gears 19, the points of meshing of the bevel gear rings 31 and 34 with each bevel gear 19 being substantially diametrically opposed upon the latter. A bladed rotor having such an actuator is disclosed in the specification of U.S. Pat. No. 3,664,763.  
  The annular hub basically comprises a rearward portion 35 from which the blade sockets 15 project and a forward portion 36 which provides the hub with its annular configuration. The forward portion and the rear ward portion are both provided with radially outwardly directed flanges 37 and 38 which are suitably bolted together with a pair of distance pieces 39 located between them. In this way an annular recess 40 is provided on the inside of the outer wall of the hub 16. This recess receives the flange 29 of the part 27 of the actuator 25. The flange 29 therefore provides a means of mounting the actuator in the hub with the ability for the part 27 to move angularly with respect to the wall of the hub about the axis 26.  
  The part 27 is provided with a forwardly extending tubular portion 41 which is itselfformed with a land 42 which incorporates a sealing ring 43. The land 42 forms a forward bearing for the part 27, and the portion 41 surrounds an annular plate 44 which forms the forward end wall of the actuator part 27.  
  A further annular plate 45 is disposed in front of the annular plate 44 and cavities as at 46 are defined between the two annular plates which house gear trains as hereinafter described.  
  Mounted in convenient manner upon the forward face of the annular plate are three gear pumps 47, 47a and 47!).  
  Each of the gear pumps comprises a pair of externally meshing gears. one gear being shown at 48. Such pumps are similar to that disclosed in the specification of US. Pat. No. 3.490.382. Each pump is driven by means of a splined quill 49 whose axis is parallel with the axis 26. Each quill 49 is connected to a spur gear 50 housed in a cavity 46 and supported for rotation in bearings 51 provided in bores in the annular plates 44 and 45.  
  The spur gear 50 associated with the pump 47 is in mesh with a spur gear 52 of smaller diameter than the spur gear 50 and mounted fast upon a shaft 53 which carries a larger spur gear 54. The shaft is mounted in bearings 55 pro\ided in bores in the annular plates 44 and 45. The spur gear 54 is in mesh with a ring of gear teeth 56 formed integrally with a hollow shaft 57 coaxial with the shaft 5. The shaft 57 extends rearwardly through and beyond the hub and at its end portion remote from the part having the ring 56 is anchored as at 58 to non-rotative structure 59 which is carried by the forward end portion of a reduction gear casing 61 of the engine.  
  The second pump 47a is similar to the pump 47 and is suitably mounted upon the plate 45 in a position spaced circumferentially from the pump 47. This second pump is likewise driven through a gear train similar to that associated with the pump 47 and associated with the ring of teeth 56.  
  Thus with rotation of the bladed rotor 6 since the shaft 57 is held fast at 58 at its rearward end. the re spcctive gears 54 rotate around the ring of teeth 56 and in consequence dri\e the first and second gear pumps 47. 4711 through the respective gears 52 and 50.  
  The first pump 47 has a lower flow capacity than the second pump 4741 so that it is concerned with pitchchange operation of the actuator at relatively slow rates. while the second pump is concerned with pro\iding additional pressure liquid for operation ofthe pitchchange actuator at fast rates.  
  The forward end portion of the shaft 57 has a radially outwardly directed flange 64 from which extends an axially directed portion 65. A ball bearing 66 is provided between the portion and an axially directed flange 67 fortned on the inner wall of the forward portion 36 of the httb 16. Between the tlangc 67 and the forward extremity 68 of the shaft 57 there is pro\ ided a sealing ring 69 of \&#39;shaped cross-scction ha ing a metallic spring ring 70. This combination forms a lifting seal arrangement whereby when the rotor is rotating at slow speeds or is stationary. the ring 69 is in fluid-sealing cngagement with the extremity 68 of the shaft. but when the speed of the rotor cyceeds a predetermined value. the centrifugal force on the sealing ring 69 is sufficient to overcome the effort of the spring ring 70 so that the sealing ring breaks contact with the extremity 68 to atoid the generation of undue friction thcrebetwecn.  
  A similar lifting seal arrangement is provided at 71 between the rearward end portion of the member 33 and a stepped tubular member 72 which is held fast in suitable manner with respect to the member 59 and thus the forward end portion 60 of the casing 6|.  
 bl l  
  The third gear pump 47b forms a feathering pump. and is mounted parallel with the other two gear pumps. being driven by a similar gear train. However, this gear train is not in mesh with the ring of teeth 56 but is instead in mesh with a ring of teeth 73 formed at the forward end portion of a tubular shaft 74 which surrounds the major length of the shaft 57 and which extends rearwardly towards the structure 59. At its rearward end portion 75 the shaft 74 is mounted in a ball bearing 76, and just forward ofthis bearing the shaft is provided with a ring of teeth 77. These teeth mesh with an idler spur gear 78 mounted for rotation in non-rotative structure at 79. The idler gear is. in turn. in mesh with a spur gear 80 also mounted for rotation in non-rotative structure and arranged to be driven through sbafting 81 by a feathering motor M mounted upon the nonrotative structure. This motor is of electrical type and brake means B are provided for locking the shafting 81 fast with respect to non-rotative structure during normal pitchchartging operation of the bladed rotor 6.  
  The annular plate 45 supports a positional control valve assembly 82 which is radially disposed and which comprises a landed spool 83 which is linearly movable within a flanged ported sleeve 84. The sleeve is mounted in roller bearings 85 in an outer sleeve 86 and a ring of gear teeth 87 is provided upon the flanged portion of the sleeve 84 by which the sleeve is in operation continuously rotatable with the two pitch-change pumps by means of gearing in mesh with the gearing associated with those pumps.  
  An input member 88 mounted in bearings 89 and 90 in non-rotative structure is suitably connected by links as at 91 to a control tube 92 which connects through a translation bearing 93 with a pivoted lever 94 mounted upon the actuator 25. A cam slot and roller arrangement 95 is associated with the lever 94 and with the spool 83. Rotary movement of the input shaft 88 effects linear movement of the tube 92 which in turn through the translation bearing 93 effects rotary movement of the lever 94. The cam slot and roller arrangement 9S translates the rotary movement of the lever 94 into linear mo ement of the spool 83.  
  Each of the gear pumps housed within the forward portion 36 of the hub 16 has a respective relief valve. the one associated with the pump 47 being generally indicated at 100. These relief valves all discharge into the hub space forward of the pumps. The discharging liquid is guided under centrifugal force into an annular reservoir 101 by way of an annular space or passage [02 which is defined by the outer wall 103 of the forward part of the portion 36 and a substantially frustocortical annular baffle or deflector 104 which is positioned inwardly of the wall 103. The baffle 104 has. upon its e tcrior forwardly facing surface. an upstanding spiral formation I05 whereby a spiral channel 106 is formed in the annular space or passage 102. An annular feathering reservoir 1010 is fortned by the baffle 104 and the feathering pump 4711 draws its liquid therefrom. The pumps 47. 47a draw their liquid directly from the reservoir 101.  
  A spinner I07 for the bladed rotor ll. and rotatable therewith has a central opening 108 at the nose portion thereof which merges into an annular divergent duct 109 formed by an inner wall 110 of the spinner and an inner cone member [[1 which fairs into the forward portion 36 of the hub 16 as shown. The wall 110 is provided with a ring of impeller blades ll2 disposed substantially in alignment with the spiral formation 105. During flight of the aircraft in which the engine is installed rarn air passes through the opening 108 and into the duct I09. thereafter passing to atmosphere towards the rear of the spinner by way of an outwardly directed duct 113, into which the duct opens. and an annular opening H4.  
  Enclosed within the forward portion 36 of the hub 16, is a condition control valve assembly. shown diagrammatically at 82a in FIG. 3, the setting of which determines the particular mode of operation of the bladed rotor. This assembly also comprises a spool and a continuously rotatable sleeve. The modes of operation in this embodiment are normal running. feathering operation. unfeathering operation and pitch-change beyond the positive range into the negative range. Operation of the spool of this condition control valve assembly is effected in a manner similar to the operation of the spool 83 by an input member (not shown) which is cireum ferentially spaced from the member 88 and also mounted in hearings in non-rotative structure. and which is co-operable with a tube 115 which connects with the spool of the condition control valve assembly by way of a translation bearing 116 and suitable cam mechanism (not shown).  
  The above construction thus provides a selfcontained bladed rotor. forming the fan ofa gas turbine engine of the ducted-fan by-pass type. which includes a reservoir. three gear pumps. two for normal pitchchanging operations and the third for feathering and unfeathering operation. positional and condition control valve means. a balanced vane-type actuator. upon one part of which the control valve means are mounted. and gearing whereby the actuator is connectcd to the blades for effecting pitch-change thereof.  
  In operation the gas turbine engine drives the bladed rotor (I. the brake means B associated with the feathcring motor drive shafting 8] being applied so that the ring of gear teeth 73 is stationary. Also the ring of gear teeth 56 is stationary by virtue of its anchorage 58 to non-rotative structure.  
  Hence. with rotation ofthe rotor all three gear pumps within the forward portion 36 of the hub [6 are driven through their respective gear trains. and provided the spool 83 is in its neutral position. as shown in the drawing. the discharge from the low flow pump 47 passes through its relief valve to reservoir by way of the spiral channel 106 provided in the annular space or passage [02. while the discharge from the high flow pump 47a is caused to pass directly to reservoir through suitable means. The spool of the condition control valve assembly 82a is. while the feathering motor brake means is applied, positioned so that the feathering pump 47h discharges its delivery through suitable by-pass means (not shown) to the reservoir. Ram air which. during flight of the aircraft. passes through the central opening of the spinner I07 is impelled by the blades H2 along the duct I09 and the duct I13 and out to atmosphere through the annular opening &#34;4. Thus cooling air is brought into heat-exchange relation by way ofthe wall 103 of the forward portion 36 of the hub 16 with the liquid discharging from the relief valve means through the spiral channel I06 to the reservoir ltll.  
  During normal running operation of the rotor the condition control valve assembly is tnaintaincd in its normal running&#34; condition.  
  When during such normal running it is required normally to adjust the pitch of the blades 12, for example in the pitch-coarsening direction. the input shaft 88 is rotated in the appropriate direction under the control of a pilots control lever. with the result that the tube 92 is displaced axially and through the translation bearing 93 adjusts the lever 94 which. in turn. through the cam slot and roller arrangement 95 adjusts the setting of the spool 83. The delivery from the low flow pump 47 which is available at the spool is now thereby directed to the coarse pitch chambers of the balanced vane-type actuator 25. while the fine pitch chambers thereof are placed in communication through suitable ducting with reservoir. Consequently the parts 27 and 28 of the actuator are angularly adjusted about the axis 26in opposite directions. Since the angular movements of these parts are equal in magnitude. but opposite in sense. the turning moments applied to the blades 12 through the gear rings 31 and 34 and the bevel gears 19 are equal and additive about the blade pitchchangc axis 17. However. since these moments are applied at positions diametrically opposite to each other upon each gear I). a balance is achieved in the journal loading of the blade root bearings 13 and [4.  
  By such displacement of the parts of the actuator 25 the blades 12 are adjusted in the coarse pitch direction to an extent dependent upon the setting of the spool 83. As the required blade pitch angle is reached the spool 83 is autormttically returned to its neutral position. Such return movement is effected by virtue of the fact that the positional control valve assembly is carried by one ofthe movable parts of the actuator and a differential effect between that part of the cam slot and roller arrangement 95 effects the necessary displacement of the spool with respect to its sleeve.  
  If. during normal running operation. the pilot moves the member 88 rapidly. consequent over travcl of the spool 83 automatically operates means (not shown) which blocks the flow to reservoir from the high flow pump 47a and causes delivery flow therefrom instead to combine with that of the low flow pump 47 whereby the liquid under pressure from both pumps now passes by way of the control valve means to the actuatorthereby achieving a faster rate of pitch change of the blades.  
  For normal pitch-fining of the blades. during normal running operation. at either slow or fast rates the me m ber 88 is moved in the opposite direction to displace the spool 83 in the direction necessary for such pitchfining.  
  When. due to an emergency in flight. or for any other reason it is required to feather the blades 12 of the bladed rotor. the fuel supply to the engine is cut off and the brake means B associated with the feathering pump motor shafting 81 is released. Simultaneously the spool of the condition control valve assembly 820 is moved by its input member (not shown) and tube llS away from its normal running&#34; position to its featherselecting&#34; position whereupon the direct flow to reservoir from the feathering pump 47/1 is blocked and delivery flow therefrom instead passes through the condition control valve assembly. As the bladed rotor loses speed. the feathering pump motor M is energized whereupon the gears and 78 drive the shaft 74. Hence the ring of teeth 73 in engagement with the gear train associated with the feathering pump 74h rotates. thereby effecting operation of the feathering pump.  
 This pump draws liquid from the feathering reservoir 101a and this liquid, which by-passes the positional control valve assembly, is directed by the condition control valve assembly to the coarse pitch chambers of the vane-type actuator 25. At the same time the fine pitch chambers ofthe actuator are placed in communication with the reservoir. Hence the blades are rapidly feathered and upon completion of the feathering operation the feathering motor is automatically de energized.  
  For subsequent unfeathering of the blades the feathering motor is again energized, the spool of the condition control valve assembly being suitably set for this operation. The feathering pump delivery flow thus passes through the condition control valve assembly and is thereafter directed through the positional control valve assembly to the fine pitch chambers of the actuator while the coarse pitch chambers are placed in communication with drain. Consequent movement of the actuator components in opposite directions effects unfeathering of the blades.  
  Suitable pitch stop means (not shown) is included within the hub 16 which must be rendered inoperative when it is required to move the blading beyond the pos itive pitch range into the negative pitch range for braking of a vehicle, for example an aircraft, in which the engine is fitted. The spool of the condition control valve assembly is movable to a further setting whereby this stop means is so rendered inoperative.  
  Although not shown in the drawings, suitable baffle means may be provided between the rings of gear teeth 56 and 73 so that if, for example due to some malfunctioning, the teeth 56 are damaged, particles thereof are less likely to reach the teeth 73 to cause further damage.  
  By so providing a single liquidpressure-operable blade-adjusting actuator disposed with its rotational axis coincident with the rotational axis of the rotor, and by so mounting the normal pitch-change pumps and the feathering pump, as well as the control valve means, on the forward side of one of the actuator parts with the annular reservoir disposed around them, a very compact form of self-contained bladed rotor is provided. Further, the annular form of the hub 16 facilitates very ready attachment of the rotor upon the output shaft of the associated engine.  
  Also by providing two pumps for normal pitchchange and a further pump for feathering and unfeathering of the blades, the further pump being drivable by the feathering motor, two independent pumping systems are present. Thus, if a failure in the operation of said two pumps for normal pitch-change occurs, due for example to some mechanical defect in the drive thereto, the feathering pump drive, being mechanically independent from that ofthose two pumps, can operate in an unimpeded manner for the feathering operation.  
  Again by providing the spiral formation which forms a spiral channel in the space formed between the relief valve means and the reservoir and by causing the liquid discharged by the relief valve means to flow through the spiral channel in heat-exchange relation with the air conducted by the ring of impeller blades 112 across the exterior surface ofthe forward portion of the hub, heat generated in the liquid upon pressure relief is dissipated into the air so conducted along the duct 109 and through the opening 114 that overheating of the liquid passing to the reservoir is avoided.  
  The invention is not limited to the provision of a baffle or deflector having a spiral formation, as in other embodiments deflectors of other form may be used, or alternatively in some bladed rotors it may only be necessary to provide the said space with cross-sectional dimensions of a particular order to achieve the desired cooling effect in the liquid discharging from the relief valve means to the reservoir.  
  In some alternative embodiments of the invention it may not be necessary to include impeller blades within the spinner structure to produce a flow of cooling air upon the exterior surface of the hub, as a simple cooling duct may instead be provided in the spinner structure. Further, in less-sophisticated installations the hub itself may project forwardly with no spinner structure surrounding it.  
  Although in the embodiment described with reference to the drawings, the two pumps for normal blade adjustment draw their liquid from the annular reservoir 101 while the pump for feathering and unfeathering draws its liquid from the feathering reservoir 1010, in other embodiments all the pumps may draw their liquid from a single reservoir.  
  The invention is not limited to the provision of pumps of gear type within the hub, as in other embodiments other suitable forms of pump may with advantage be used.  
  Further, the invention is not limited in its application to fans of gas turbine engines of the ducted-fan by-pass type, as in other embodiments of the invention such bladed rotors may be intended for installation in other machines where it is also desirable for those rotors to each be of self-contained form carrying, so as to be rotatable therewith, a liquid reservoir, one or more pumps and an actuator.  
 I claim:  
  1. A bladed rotor, suitable for a gas turbine engine of the by-pass type, including a hub which carries, so as to be rotatable therewith, a liquid reservoir, at least one pump operable upon rotation of the rotor, relief valve means associated with said pump, and an actuator for adjusting the blades of the rotor to vary flow of fluid over the blades, said pump, when operating, drawing liquid from the reservoir and delivering it under pressure to said actuator, and liquid discharged by the relief valve means in flowing to the reservoir passing adjacent to an outer wall of the hub.  
  2. A rotor as claimed in claim 1, wherein flow from said relief valve means to the reservoir is by way of means defining a spiral channel.  
  3. A rotor as claimed in claim 2, wherein means is provided externally of said hub whereby air is brought into heatexchange relation, by way of said outer wall of the hub, with the liquid passing along said spiral channel.  
  4. A rotor as claimed in claim 3, wherein said means provided externally ofthe hub comprises ducting which incorporates impeller blading formed as part of spinner structure, said spinner structure being attachable to the hub for rotation therewith.  
  S. A rotor as claimed in claim 1, wherein the relief valve means comprises a respective relief valve disposed in the casing of said pump.  
  6. A rotor as claimed in claim 3, wherein mechanical means connect said pump with non-rotative structure external of the rotor to afford its operation upon rotation of the rotor.  
  7. A rotor as claimed in claim 6, wherein said mechanical means includes gearing, also carried by the hub, and shafting coaxial with the hub and extending from the gearing to said non-rotative structure.  
  8. A rotor as claimed in claim 1, wherein said actuator is of vane-type, having its axis of rotation coincident