U.S. patent number 3,729,957 [Application Number 05/210,490] was granted by the patent office on 1973-05-01 for fan.
This patent grant is currently assigned to The Secretary of State for Defence, in Her Britannic Majesty's. Invention is credited to Kenneth Edward George Bracey, James Alexander Petrie.
United States Patent |
3,729,957 |
Petrie , et al. |
May 1, 1973 |
FAN
Abstract
A fan comprises first and second rotor stages driven through a
differential ear. The first stage is driven from the sun gear of
the differential while the second stage is driven from the annulus
gear of the differential. The planet carrier is driven from drive
means. The invention is particularly applicable to gas turbine
engines in which case the first stage of the fan may comprise a hub
compressor and the drive means may comprise a gas turbine.
Inventors: |
Petrie; James Alexander
(Littleover, EN), Bracey; Kenneth Edward George
(Findern, EN) |
Assignee: |
The Secretary of State for Defence,
in Her Britannic Majesty's (London, EN)
|
Family
ID: |
9713823 |
Appl.
No.: |
05/210,490 |
Filed: |
December 21, 1971 |
Foreign Application Priority Data
Current U.S.
Class: |
60/226.1; 60/268;
415/79; 415/122.1; 416/193R; 60/39.183; 74/665K; 415/199.4;
416/201R |
Current CPC
Class: |
F04D
25/028 (20130101); F04D 19/026 (20130101); F02K
3/06 (20130101); F02C 7/04 (20130101); F01D
5/022 (20130101); Y10T 74/19121 (20150115); Y02T
50/60 (20130101); Y02T 50/673 (20130101) |
Current International
Class: |
F02C
7/04 (20060101); F04D 19/02 (20060101); F01D
5/02 (20060101); F02K 3/00 (20060101); F04D
19/00 (20060101); F02K 3/06 (20060101); F02k
003/06 (); F16h 037/06 () |
Field of
Search: |
;60/226R,268,39.16C
;415/65,79,122 ;74/15.2,750,665K |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Hart; Douglas
Claims
We claim:
1. A fan comprising a first and a second rotor stage in flow series
and a differential gear comprising a sun gear, a plurality of
planet gears carried from a planet carrier, and an annulus gear,
first connection means by which the first rotor stage is connected
to the sun gear, second connection means by which the second rotor
stage is drivingly connected to the annulus gear and drive means
connected to rotate the planet carrier.
2. A fan as claimed in claim 1 and in which said first rotor stage
comprises a bladed hub compressor, and the second stage comprises a
main bladed rotor stage, the blades of the hub compressor extending
over only the central portion of the main rotor stage.
3. A fan as claimed in claim 2 and in which there is a shroud round
the blades of the hub compressor.
4. A fan as claimed in claim 3 and in which the hub compressor
shroud is carried from the main rotor stage and extends forwardly
to encompass the hub compressor.
5. A fan as claimed in claim 1 and in which said drive means
comprises a gas turbine.
6. A fan as claimed in claim 5 and in which said fan drive gas
turbine is driven by the exhaust gas of a gas generator.
7. A fan as claimed in claim 6 and in which said gas generator
comprises a gas turbine gas generator.
8. A fan as claimed in claim 7 and in which said gas generator has
an air intake, the rotors being mounted coaxially ahead of the
intake so that the fan compresses air which provides by-pass air
and supercharged inlet air to the gas generator.
9. A fan as claimed in claim 8 and in which said gas turbine gas
generator comprises a multi-shaft gas generator.
Description
This invention relates to a fan which is particularly but not
exclusively useful in a gas turbine engine.
Fans having large capacity are useful in a number of applications
and particularly in high by-pass ratio gas turbine engines. To
produce the high capacity it has been the practice to increase the
overall diameter of the fans, while to reduce complications
entailed with very large hubs it has been the practice to make the
hub of a fairly small size. A problem then arises in that to avoid
the production of large amounts of noise the tip speed of the fan
blades must be less than the speed of sound; this therefore puts a
limit on the rotational speed of the fan and consequently causes
the inner sections of the fan blades to be moving so slowly that it
is difficult to cause them to operate effectively. One solution
which has been proposed is to provide an additional fan stage whose
diameter is considerably less than that of the main fan, this hub
compressor being driven with the main fan or in some cases by a
separate turbine.
The hub compressor then restores the efficiency of the central
portion of the fan, but entails some complication in drive.
The present invention provides a fan having such a hub compressor
and having a very simple drive which divides the torque available
between the main fan and the hub compressor.
According to the present invention a fan comprises a first and
second rotor stage in flow series and a differential gear
comprising a sun gear, a plurality of planet gears carried from a
planet carrier, and an annulus gear, the first rotor stage being
connected to the sun gear, the second rotor stage being drivingly
connected to the annulus gear and drive means connected to rotate
the planet carrier.
Said first rotor stage may comprise a hub compressor and said
second stage may comprise a main rotor stage, the blades of the hub
compressor extending over only the central portion of the main
rotor stage.
In the case of a gas turbine engine the drive means will normally
comprise a turbine of the engine.
The hub compressor is preferably shrouded; thus the shroud may be
carried from the main rotor stage and extend forwardly to encompass
the hub compressor.
In a preferred embodiment the fan is mounted coaxially with a gas
generator section so that the fan compresses air which provides
by-pass air and also supercharged inlet air to the gas generator.
In our preferred case the gas generator is a two-shaft gas
generator and comprises a low pressure turbine which drives the
planet carrier.
The invention will now be described merely by way of example with
reference to the accompanying drawings in which:
FIG. 1 is a partly broken away view of a gas turbine engine having
a fan in accordance with the invention and
FIG. 2 is an enlarged view of the fan portion of the engine of FIG.
1.
FIG. 1 shows a gas turbine engine comprising a gas generator
section 10 and a fan generally indicated at 11. The fan compresses
air part of which supercharges the gas generator 10 while the
remainder passes between the gas generator and a fan cowl 12 to
provide propulsive thrust. It will be seen that the gas generator
is a two-shaft gas generator; that is it comprises intermediate
pressure and high pressure compressors 13 and 14 drivingly
connected to intermediate and high pressure turbines 16 and 15
respectively. A third, low pressure turbine 17 is provided and
drives an LP shaft 18 which extends coaxially inside the gas
generator shafts to drive the fan.
The arrangement of the fan is best seen in FIG. 2. The fan
comprises a main fan rotor 20 made up of a plurality of blades
which carry part way along their extent a shroud ring 21. Within
the shroud ring 21 and upstream of the main fan rotor 20 there is a
hub compressor 22 which again comprises a plurality of rotor blades
which only extend over the central part of the main fan rotor
20.
The hub compressor 22 is driven from a shaft 23 which is mounted in
bearings 24 and 25. The bearing 24 supports the shaft 23 from the
shaft 26 of the main fan 20, and this shaft is in turn supported by
the bearing 27 from fixed structure of the engine. In addition to
these bearings, the shaft 26 supports bearings 29 and 30 whose
purpose will become apparent below.
To drive the shafts 23 and 26, the shaft 23 is provided with an
external set of teeth at 31 which form the sun wheel of an
epicyclic differential gear. The shaft 26 is attached to an annulus
gear 32 whose internal teeth form the annulus gear of the same
differential. A plurality of pinions 33 mesh between the sun gear
31 and annulus 32, these components being carried on a pinion
carrier 34. The carrier is extended forwardly to mount within the
bearing 29 mentioned above, while the rearward portion extends to
form the LP shaft 18. This rearward extension is supported in the
bearing 30 and itself supports the bearing 25 of the shaft 23.
Operation of the system is as follows:
Shaft 18 is driven by the LP turbine and consequently drives the
planet carrier 34. Rotation of this carrier causes the pinions to
rotate about the fan axis and causes equal driving loads to be
exerted on the sun wheel 31 and the annulus gear 32. Because of the
difference in the diameters of these wheels, a greater torque will
be exerted on the annulus gear than on the sun wheel; consequently
more power is passed into the main fan rotor than into the hub
compressor. This is the desired splitting of work.
The aerodynamics of the fan and hub compressor are arranged so that
at designed speed for the turbine the fan will rotate at a fairly
slow speed, thus avoiding any danger of sonic or near sonic fan
speeds which would produce noise. The hub compressor is arranged to
rotate considerably faster, since with its relatively small
diameter blades there is little chance of its blades going sonic.
Since the hub compressor rotates at a relatively high speed it can
be reasonably efficient over its radial extent; it therefore makes
up for the relative inefficiency of the central section of the fan
blades. In fact the inner portion of the fan blades may be made
simply as struts which perform no work on the air which has been
compressed by the hub compressor.
It will be appreciated that the sun gear, planet carrier and
annulus gear all rotate in the same direction, the differential
speed between the sun and annulus gears being taken up by rotation
of the pinions. It will be understood by those skilled in the art
that the arrangement in which these gears rotate in the same sense
produces considerably less friction loss than a gear in which
components contra-rotate. Thus our present arrangement reduces
frictional losses to a sixth of a conventional epicyclic gear
arrangement. Such a reduction is of the greatest importance in
applications where the transmitted power is very high since
frictional losses which appear as heat in the lubricating fluid
cause great difficulty in rejecting heat in sufficient
quantities.
It will be appreciated that this invention is particularly relevant
to the fans of gas turbine engines but can be applied to other
fans, particularly propulsive fans which may be used for VTO
application etc. In any of these cases it is only necessary to
provide the drive in the form of a single shaft, the gear
arrangement of the invention providing the necessary splitting of
power.
* * * * *