U.S. patent number 3,870,434 [Application Number 05/427,377] was granted by the patent office on 1975-03-11 for gear arrangement for variable pitch fan.
This patent grant is currently assigned to General Electric Company. Invention is credited to Elmir Edward Paulson.
United States Patent |
3,870,434 |
Paulson |
March 11, 1975 |
**Please see images for:
( Certificate of Correction ) ** |
Gear arrangement for variable pitch fan
Abstract
A variable pitch fan having a plurality of circumferentially
spaced apart variable pitch fan blades journalled for rotation
about their longitudinal axes in a hub member, further includes a
plurality of sector gears drivably connected to the rotor blades
and simultaneously actuated by a unison bevel gear wherein each
sector gear operates to apply its highest torque to the blades
during the cruise mode of engine operation when the inherent
turning moments from the centrifugal forces operating on the blades
are at their peak.
Inventors: |
Paulson; Elmir Edward
(Topsfield, MA) |
Assignee: |
General Electric Company (Lynn,
MA)
|
Family
ID: |
23694608 |
Appl.
No.: |
05/427,377 |
Filed: |
December 21, 1973 |
Current U.S.
Class: |
416/160; 415/130;
416/147; 416/215; 415/129; 416/131; 416/162 |
Current CPC
Class: |
F01D
7/00 (20130101); F05D 2260/76 (20130101); F05D
2220/36 (20130101); F05D 2260/74 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F01D
7/00 (20060101); B63h 003/06 () |
Field of
Search: |
;416/160
;74/416-417,393 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Lawrence; Derek P.
Claims
What is claimed is:
1. In a turbomachine of the type having plurality of spaced apart
variable pitch blades, journalled in a rotable hub member, a gear
arrangement comprising:
a plurality of spaced apart sector gears in respective driving
engagement with the blades wherein each gear has a plurality of
teeth spaced apart at varying distances along the length of a
conical surface of revolution,
said sector gears arranged such that the spaced apart teeth of any
two adjacent gears overlap without engaging each other, and
a unison bevel gear having a plurality of circumferentially spaced
apart teeth in simultaneous driving engagement with the teeth of
the sector gears.
2. The turbomachine of claim 1 wherein the angle at which the
conical surface of revolution intersects the center axis of hub
rotation coincides with the angle at which the teeth of the unison
bevel gear would intersect the center axis of rotation.
3. The turbomachine of claim 2 wherein the teeth of the sector
gears evolve in a spiraling helix and are of shorter longitudinal
length than the teeth of the unison bevel gear and thus engage the
bevel gear at varying radial distances from the center axis of
rotation with changes in blade pitch.
4. In a gas turbine engine having a variable pitch fan with a
plurality of circumferentially spaced apart variable pitch fan
blades, each of which includes an airfoil vane portion together
with a root journalled about an inner hub member for rotatable
adjustment, an actuating gear arrangement comprising:
a plurality of circumferentially spaced apart sector gears in
respective driving engagement with the blade roots wherein each
gear has a plurality of teeth spaced apart at varying distances
along the length of a conical surface of revolution,
said sector gears arranged such that the spaced apart teeth of any
two adjacent gears overlap without engaging each other, and
a unison bevel gear disposed for rotation about the longitudinal
engine center axis and having a plurality circumferentially spaced
apart teeth disposed about the outer periphery thereof for
simultaneous driving engagement with the teeth of the sector
gears.
5. The gear arrangement of claim 4 wherein the angle at which the
conical surface of revolution intersects the longitudinal engine
center axis coincides with the angle at which the teeth of the
unison bevel gear would intersect the engine center axis.
6. The gear arrangement of claim 5 wherein the teeth of the sector
gears evolve in a spiraling helix and are of shorter longitudinal
length than the teeth of the unison bevel gear and thus engage the
bevel gear at varying radial distances from the center axis of the
engine with changes in blade pitch.
7. The gear arrangement of claim 6 wherein:
the teeth of each sector gear which engage the teeth of the unison
gear are at the outer end of the helical spiral during the cruise
mode of engine operation so as to apply the greatest torque to the
blade roots when the inherent turning moments from the high
centrifugal forces operating on the blades are at their peak;
and variation in blade pitch toward flat pitch and reverse pitch
operates to move the engaging teeth of each sector gear radially
and diametrically inward along the conical surface of revolution
such that the outer ends of the teeth of the sector gears which
engage the unison bevel gear during the cruise position do not
interfere with adjacent sector gears, but instead overlap the
adjacent sector gears in a non-interfering manner.
Description
BACKGROUND OF THE INVENTION
This arrangement relates to a gear arrangement for a variable pitch
fan and, more particularly, to sector gear arrangement for
simultaneously varying the pitch of a plurality of spaced apart
variable pitch fan blades journalled in a hub member.
During normal operation of a variable pitch fan, the individual fan
blades incur a high dynamic turning moment due to the high
centrifugal forces which operate to rotate the blades about their
longitudinal center axes such that the major surfaces of each
airfoil vane tend to become aligned normal to the center axis of
rotation and thus block the airflow through the fan blades.
Additional information regarding the inherent turning moments of
variable pitch fan blades may be found in U.S. Pat. No. 2,844,303
dated July 22, 1958.
As is well known in the art, the inherent turning moments incurred
by variable pitch fan blades must be countered by an opposing force
which may be provided by counterbalance weights. Various schemes
for such counterbalance weights have been proposed and are well
known in the patent literature. However, the inclusion of any type
of scheme for counterbalance weights within a rotating fan
substantially increases the weight of the rotating components, thus
reducing the overall efficiency of the fan. In the gas turbine art
where variable pitch fan engines have been recently proposed, such
increased weight is unsatisfactory and detracts from the overall
efficiency of the engine.
In a variable pitch fan where the individual fan blades have
inwardly extending root portions journalled about a central hub
member, it is common practice to provide individual sector gears
drivably engaged to the blade roots for simultaneously varying
blade pitch. The individual sector gears are in turn engaged by a
driving unison gear. Increasing the size of the individual sector
gears can operate to increase the effective actuating torque
applied to the blades and hence counterbalance the inherent turning
moments operating on the individual fan blades. However, the size
of the sector gears has heretofore been limited by the spacing
between adjacent blades and thus failed to provide the adequate
actuating torque and/or angles of rotation required to
counterbalance the inherent turning moments.
Therefore, it is a primary object of this invention to provide a
sector gear arrangement for a turbofan engine through which a high
actuating torque may be applied to variable pitch fan blades during
the cruising mode of operation where the inherent turning moment is
greatest, thus eliminating the need for balance counterweights.
It is also an object of this invention to provide a sector gear
arrangement for a variable pitch turbofan engine wherein the teeth
of adjacent sector gears overlap in a non-interfering manner so as
to provide the high actuating torque required to counterbalance the
inherent turning moment together with the necessary angles of
rotation.
SUMMARY OF THE INVENTION
These and other objects and advantages will be more clearly
understood from the following detailed description and drawings,
all of which are intended to be representative of, rather than in
any way limiting on, the scope of invention. The gear arrangement
of this invention is provided for a turbomachine of the type having
a plurality of spaced apart variable pitch blades journalled in a
rotatable hub member. The gear arrangement includes a plurality of
spaced apart sector gears in respective driving engagement with the
blades wherein each gear has a plurality of teeth spaced apart at
varying distances along the length of a conical surface of
revolution. There is also provided a unison bevel gear also having
a plurality of circumferentially spaced apart teeth for
simultaneously engaging the teeth of the sector gears.
DESCRIPTION OF THE DRAWINGS
While the specification concludes with claims distinctly claiming
and particularly pointing out the invention described herein, it is
believed that the invention will be more readily understood by
reference to the discussion below and the accompanying drawings in
which:
FIG. 1 is a partial cross-sectional view of the gear arrangement
and variable pitch fan of this invention.
FIG. 2 is a partial perspective view of the gear arrangement and
variable pitch fan of FIG. 1.
FIG. 3 is a partial perspective view of the cruise mode of
operation for the gear arrangement and variable pitch fan of FIG.
1.
FIG. 4 is a partial perspective view of the transition mode of
operation for the gear arrangement and variable pitch fan of FIG.
1.
FIG. 5 is a partial perspective view of the reverse mode of
operation for the gear arrangement and variable pitch fan of FIG.
1.
FIG. 6 is a partial perspective view of an alternate embodiment of
the gear arrangement and variable pitch fan of FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to FIG. 1, there is shown an arrangement for a variable
pitch fan 10 which is suitable for attachment to the forward end of
a gas turbine engine (not shown). Although the invention is herein
described in relation to a variable pitch fan, it will be readily
understood to have broader application to other types of axial flow
turbomachinery wherein blades are journalled in a rotatable hub
member with each blade being adjustably rotatable along its
longitudinal axis. The variable pitch fan 10 includes a plurality
of circumferentially spaced apart variable pitch fan blades 12
disposed about an inner fairing 14 which extends forwardly of the
variable pitch blades 12 and defines an upstream spinner 16. A
static bypass duct 11 is provided between the inner fairing 14 and
an outer spaced apart cowling 13.
The gas turbine engine may be of a conventional type having a
compressor section, a combustion section (not shown), and a turbine
section (not shown) arranged in serial flow relation on either a
single shaft or a dual shaft (not shown). The variable pitch fan
blades 12, together with the inner fairing 14 and the spinner 16,
are all interconnected for rotation about a longitudinal engine
center axis A by a rotating frame structure (also not shown) as is
well known in the gas turbine art. The outline of only the forward
end of the compressor is illustrated at 18 and defines a compressor
inlet 20 communicating with a plurality of rotatable compressor
blades 22 interspaced between a plurality of stator vanes 24 which
may be of the variable type. The compressor is thus charged by a
portion of the airflow emanating from the fan 10 and the variation
of blade pitch not only varies bypass ratio but in effect provides
a variable first compressor stage. A plurality of circumferentially
spaced apart stator vanes 24 may be mounted between the inner
fairing 14 and the outer cowling 13 aft of the variable pitch fan
blading 12 and ahead of the compressor inlet 20. The pitch of the
fan blading 12 may be varied to reverse the airflow along the duct
11 and thus provide reverse thrust to aerodynamically brake a
landing aircraft.
Each variable pitch fan blade 12 includes an airfoil vane portion
26 extending radially outward from a platform 28 which overhangs an
inwardly directed root section 30. Each root section 30 preferably
includes a plurality of radially inwardly directed, spaced apart,
tangs 32 which are maintained in pinned interspaced relation with a
second plurality of tangs 34 extending radially outward from a root
shaft 35. The interspaced tangs 32 and 34 are maintained in pinned
relation by a longitudinally extending pin 36 which extends through
a plurality of coaxially spaced apart holes in the tangs 32,
34.
The pinning of variable pitch fan blades has been found to be
advantageous from a vibrational point of view and such pinned
blades appear to survive under conditions which would ordinarily
promote the rapid failure of fixed root blades. In addition,
pinning variable pitch fan blades provides an easy means for
removing and replacing the fan blades. It should also be
appreciated that small clearances may be provided between the pin
receiving holes and the pins 36 so as to permit some rigid body
motion through the rolling or slipping together of contacting
surfaces. Also, by changing the pin clearances, considerable
control may be had over the resonant characteristics without having
to redesign the airfoil vane section 26. Although the variable
pitch fan blades have been described in a preferred embodiment with
pinned roots, it will be readily apparent that the variable pitch
fan blades could also be retained by conventional dovetail
roots.
The root shaft 35 of each variable pitch fan blade 12 is thickened
at its inner radial end to form a circumferential flange 37 which
engages a plurality of circumferentially spaced apart anti-friction
bearings 38. The rotating structure includes a reinforced
cylindrical support or hub section 40 which has a plurality of
circumferentially spaced apart radial bores 42 therethrough, each
one of which receives a root shaft 35 from a variable pitch fan
blade 12. The radial bores 42 each include an overlapping
circumferential flange portion 44 aligned in substantially opposing
relation to a corresponding circumferential flange 37 so as to
maintain the anti-friction bearings 38 therebetween. In this
manner, each blade is maintained for rotation about its center axis
B at the high centrifugal load forces which are incurred during
high speed operation of the fan 10.
Referring now to FIG. 2, in conjunction with FIG. 1, there are
shown a plurality of circumferentially spaced apart sector gears 46
extending radially inward from integral connection with the root
shafts 35. Each of the sector gears 46 includes a plurality of
circumferentially spaced apart teeth 52 extending from the outer
periphery thereof for engagement with a second plurality of
circumferentially spaced apart teeth 50 disposed around the
periphery of a unison bevel gear 48. During engine and fan
operation, the unison bevel gear 48 may be controlled by
conventional means to rotate about the longitudinal engine axis A
independently of fan rotation. Thus, it will be apparent that a
change in the angular position of the unison bevel gear 48 with
respect to the support section 40 operates to simultaneously rotate
all the spaced apart sector gears 46 about their longitudinal axes
B. Rotation of all the sector gears 46 about their longitudinal
axes B simultaneously varies the pitch of all the fan blades 12. In
this manner, the pressure ratio across the fan blades 12 may be
varied to meet the different engine operating requirements as the
flight mission dictates.
During fan operation, the individual fan blades 12 incur a high
dynamic turning moment due to the high centrifugal forces which
operate to rotate the blades about their longitudinal center axes B
such that the major surfaces of each airfoil vane 26 tend to become
aligned normal to the engine center axis A of fan rotation and thus
block the airflow through the static bypass duct 11. For additional
information regarding inherent turning moments of variable pitch
fan blades, please refer to U.S. Pat. No. 2,844,303 dated July 22,
1958.
As is well known in the art, the inherent turning moments incurred
by variable pitch fan blades must be countered by an opposing force
which may be provided by counterbalance weights. Various schemes
for such counterbalance weights have been proposed and are well
known in the patent literature. However, as previously discussed,
the inclusion of any type of scheme for counterbalance weights
within a rotating fan substantially increases the weight of the
rotating components, thus reducing the overall efficiency of the
fan.
Increasing the size of the individual sector gears can also operate
to increase the effective actuating torque applied to the blades
and hence counterbalance the inherent turning moments operating on
the individual variable pitch fan blades. However, the size of the
sector gears has heretofore been limited by the spacing between
adjacent blades and thus failed to provide the adequate actuating
torque required to counterbalance the inherent turning moments.
The individual sector gears of this invention, however, have been
specially designed to provide a high actuating torque at the normal
cruise position of the variable pitch fan blades where the inherent
turning moment is greatest, thus eliminating the need for any type
of counterbalance weights. Referring now especially to FIG. 2, it
can be seen that the teeth 52 of the sector gear 46 evolve in a
spiraling helix about a conical surface of revolution shown
generally by the phantom line 54 around the blade longitudinal axis
B. The teeth 52 are of shorter longitudinal length than the teeth
50 of the unison bevel gear 48 and thus engage the bevel gear at
varying radial distances from the engine center axis A with changes
in blade pitch. In the preferred embodiment herein depicted, it is
not necessary that the teeth 52 evolve a full 360.degree. about the
conical surface 54 in view of the limited range of variation of
blade pitch required for normal engine operation. However, for
other applications it would be possible to evolve the teeth 52
through a full 360.degree. or more depending upon the amount of
variation in blade pitch desired.
Referring now to FIG. 3 in conjunction with the solid line airfoil
vane 26 of FIG. 2, there is shown the cruise position for the
variable pitch fan blades 12 wherein the inherent turning moments
due to the high centrifugal forces operating on the blades are at
their peak. It will be readily appreciated that the teeth 52 which
are engaged with the teeth 50 of the unison bevel gear 48 during
the cruise position are at the outer end of the helical spiral, and
hence apply the greatest turning moment to the root shaft 35 due to
their increased diametral distance from the longitudinal blade axis
B. Despite the increased diametral distance of the teeth 52 engaged
with the teeth 50 of the unison bevel gear 48, there can be seen to
be no interference between the non-engaged teeth 52 of adjacent
sector gears 46. As is readily apparent, the angle at which the
teeth 50 of the unison bevel gear 48 would intersect the engine
center axis A must coincide with the angle at which the conical
surface of revolution 54 intersects the engine center axis A. The
teeth 50 and 52 may be straight, tapered, or angled, depending upon
the configuration desired.
Turning now to FIG. 4, in conjunction with the phantom line airfoil
vane section 56 of FIG. 2, there is shown the position assumed by
the variable pitch fan blades 12 at the instant of transition from
a forward mode of propulsion to a reverse mode of propulsion. The
individual sector gears 46 have been rotated in a clockwise
direction as viewed from the top of the variable pitch fan blades
12 and the teeth 52 engaged by the teeth 50 of the bevel gear 48
have moved radially and diametrically inward along the conical
surface of revolution indicated by the phantom line 54. It should
be readily understood that the clockwise direction of rotation has
only been arbitrarily established for purposes of illustration and
that a counterclockwise direction of rotation would be equally
suited for purposes of this invention. The magnitude of the torque
applied to the sector gears 46 by the bevel gear 48 has also
correspondingly decreased due to the shortening of the effective
moment arms between the bevel gear and the blade longitudinal axis
B. The major surfaces of the airfoil vanes 26 are also aligned
normal to the engine center axis A (flat pitch) and hence the
effects of the inherent turning moments which normally operate to
rotate the blades about their longitudinal center axis B is
negligible. Referring particularly to FIG. 4, it can be seen that
the outer ends of the teeth 52 which initially engaged the unison
bevel gear 48 during the cruise position do not interfere with the
adjacent sector gears during blade rotation, but instead overlap
the adjacent sector gears in a non-interfering manner.
Referring now to FIG. 5, in conjunction with the phantom line
airfoil vane section 58 of FIG. 2, there is shown the position
assumed by the variable pitch fan blades 12 during the reverse
thrust mode of operation when the direction of airflow through the
bypass duct 11 is reversed. The teeth 52 which engage the teeth 50
of the unison bevel gear 48 have been rotated to their radial and
diametral inner limit while the non-engaged portions of the teeth
52 overlap adjacent sector gears 46 in a non-interfering manner.
The torque applied to the sector gears 52 is at its minimum which
is entirely satisfactory due to the reduction in the inherent
dynamic turning moment which operates on the blades during reverse
pitch.
Accordingly, while a preferred embodiment of the present invention
has been depicted and described, it will be appreciated by those
skilled in the art that many modifications, substitutions and
changes may be made thereto without departing from the invention's
fundamental theme. For example, although the teeth 52 are arranged
in spaced apart relation along a helical spiral, it will be readily
appreciated that the teeth 52 may also be spaced apart in any
manner along the length of the conical surface of revolution 54 so
long as the teeth of the bevel gear 48 are sufficiently long to
engage all the teeth of the sector gear. Thus, there may be a
discrete jump from one tooth of the sector gear to an adjacent
tooth as shown in the alternate embodiment of FIG. 6, where a
sector gear 46' includes two distinct tiers of teeth 52' for
engagement with the unison bevel gear 48. Thus having described
preferred embodiments of the invention, though not exhaustive of
all possible equivalents, what is desired to be secured by Letters
Patent is distinctly claimed and particularly pointed out in the
claims appearing below.
* * * * *