U.S. patent number 3,869,221 [Application Number 05/443,189] was granted by the patent office on 1975-03-04 for rotor wheel fan blade adjusting apparatus for turbojet engines and the like.
This patent grant is currently assigned to Motoren-und Turbinen-Union Munchen GmbH. Invention is credited to Walter Wildner.
United States Patent |
3,869,221 |
Wildner |
March 4, 1975 |
ROTOR WHEEL FAN BLADE ADJUSTING APPARATUS FOR TURBOJET ENGINES AND
THE LIKE
Abstract
A fan blade adjusting apparatus for adjusting fan blades on a
rotor wheel of a turbojet engine of the type having compressor
blades and fan blades arranged radially spaced from one another on
a common rotatable rotor wheel with the compressor blades supplying
air to a primary flow duct of the engine and with the fan blades
supplying air to a secondary flow duct of the engine.
Piston-cylinder arrangements are arranged in the annular space
between the primary and secondary flow ducts for imparting axial
movement to an annular member attached by way of pivotal arms to
the fan blades such that axial movement of the annular member
effects pivotal adjustment of the fan blades. The annular member is
attached to and rotatable with the rotor wheel and the forces are
transferred from the piston-cylinder arrangement by way of an
antifriction bearing having the outer race rotatably fixed but
axially movable by way of the piston-cylinder arrangement and an
inner race which moves rotatably and axially with the annular
member. The fixed casing of the engine in the annular space
includes guide elements and open spaces for permitting axial
movement of the bearing and associated structure while radially
supporting same.
Inventors: |
Wildner; Walter (Munich,
DT) |
Assignee: |
Motoren-und Turbinen-Union Munchen
GmbH (Munich, DT)
|
Family
ID: |
5872104 |
Appl.
No.: |
05/443,189 |
Filed: |
February 19, 1974 |
Foreign Application Priority Data
|
|
|
|
|
Feb 16, 1973 [DT] |
|
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2307656 |
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Current U.S.
Class: |
415/130;
416/157R; 60/226.1; 416/168R |
Current CPC
Class: |
F01D
7/00 (20130101); F05D 2260/76 (20130101); F05D
2260/74 (20130101); F05D 2220/36 (20130101) |
Current International
Class: |
F01D
7/00 (20060101); F01d 007/00 () |
Field of
Search: |
;415/129,130,141,140
;416/157,156,162,166 ;60/226R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Craig & Antonelli
Claims
I claim:
1. Fan blade adjusting apparatus for adjusting fan blades on a
rotor wheel of a fluid flow machine of the type having compressor
blades and fan blades circumferentially around said compressor
blades on a common rotatable rotor wheel with the compressor blades
supplying fluid to a primary flow duct of the flow machine and with
the fan blades supplying fluid to a secondary flow duct of said
flow machine; said apparatus comprising:
bearing means including an inner bearing race, an outer bearing
race, and antifriction means interposed between said inner and
outer races for permitting relative rotation of said races with
respect to one another about the axis of rotation of the rotor
wheel,
actuating force applying means engageable with one of said inner
and outer races for axially moving said bearing means,
actuating force transmitting means connected to and movable with
the other of said inner and outer races,
and coupling means for coupling said transmitting means to said fan
blades such that axial movement of said transmitting means effects
pivotal adjustment of said fan blades about fan blade pivot axes
extending transverse to said axis of rotation of the rotor
wheel.
2. Apparatus according to claim 1, wherein said primary and
secondary flow ducts extend coaxially to said axis of rotation of
the rotor wheel, and wherein said bearing means, actuating force
applying means, and actuating force transmitting means are disposed
in an annular space between said primary and secondary flow
ducts.
3. Apparatus according to claim 1, wherein said flow machine
includes a fixed casing, wherein said force applying means includes
a first portion fixed to said casing and a second portion which is
connected to said one of said inner and outer races and is axially
movable with respect to said fixed portion.
4. Apparatus according to claim 3, wherein relatively fixed axially
extending guide means are connected to said fixed casing for
slidably guiding axial movement of said bearing means while also
radially flexibly supporting said bearing means.
5. Apparatus according to claim 4, wherein said second portion
includes ring elements which engage axially facing shoulders of
said one of said inner and outer races, and wherein an extension of
one of said ring elements includes way means which are axially
slidably guided in teeth means of said fixed guide means.
6. Apparatus according to claim 5, wherein said fixed guide means
includes guide extensions positioned radially inwardly and
outwardly of the respective inner and outer races for radially
guiding said bearing means and for forming recess means
accommodating axial movement of said bearing means.
7. Apparatus according to claim 1, wherein said actuating force
applying means is engageable with said outer race and said
transmitting means is connected to and movable with said inner
race.
8. Apparatus according to claim 7, wherein said actuating force
applying means includes a piston and cylinder movable with respect
to one another, with one of said piston and cylinder being attached
to a fixed casing of the flow machine and the other of said piston
and cylinder being connected to said outer race for movement
therewith.
9. Apparatus according to claim 1, wherein said flow machine is a
turbojet engine, said primary flow duct leading to combustion
chamber means of said engine and said secondary flow duct being
arranged in bypassing relationship to said primary flow duct for
applying thrust forces to said engine.
10. Apparatus according to claim 9, wherein said fan blades are
arranged radially outwardly of said compressor blades and are
pivotal about said pivot axes independently of the compressor
blades.
11. Apparatus according to claim 6, wherein said flow machine is a
turbojet engine, said primary flow duct leading to combustion
chamber means of said engine and said secondary flow duct being
arranged in bypassing relationship to said primary flow duct for
applying thrust forces to said engine.
12. Apparatus according to claim 9, wherein said actuating force
applying means includes a piston and cylinder movable with respect
to one another, with one of said piston and cylinder being attached
to a fixed casing of the flow machine and the other of said piston
and cylinder being connected to said outer race for movement
therewith.
13. Apparatus according to claim 1, wherein said transmitting means
includes an annular member, wherein said fan blades include
actuating levers extending radially with respect to their
respective blade pivot axes, and wherein said actuating levers are
connected to said annular member by way of articulated bearings
such that axial movement of said annular member results in pivotal
movement of said actuating levers.
14. Apparatus according to claim 1, wherein said actuating force
applying means includes one of hydraulic operated means,
pneumatically operated means and electromagnetic operated
means.
15. Apparatus according to claim 1, wherein said actuating force
applying means includes a plurality of fluid operated
piston-cylinder systems which extend parallel to said axis of
rotation of the rotor wheel and which are spaced circumferentially
equally from one another about said axis.
16. Apparatus according to claim 10, wherein said transmitting
means includes an annular member, wherein said fan blades include
actuating levers extending radially with respect to their
respective blade pivot axes, and wherein said actuating levers are
connected to said annular member by way of articulated bearings
such that axial movement of said annular member results in pivotal
movement of said actuating levers.
17. Apparatus according to claim 16, wherein said actuating force
applying means includes a plurality of fluid operated
piston-cylinder systems which extend parallel to said axis of
rotation of the rotor wheel and which are spaced circumferentially
equally from one another about said axis.
Description
BACKGROUND AND SUMMARY OF THE INVENTION
This invention relates to apparatus for varying or adjusting the
inclination of fan blades on a turbojet engine rotor wheel of the
type designed to pass different concentric mass flows.
In modern turbojet engines a greater portion of the available
engine thrust is frequently provided by axial-flow fans of
relatively large diameter.
The use of these axial-flow fans permits bypass ratios -- relative
to the core engine unit of the respective jet engine -- to be
achieved as high as 10:1 or over.
With such bypass ratios a particularly useful practice has been to
adapt the fan to the changed conditions at cruise flight by making
the inclination of the fan blades variable and thus optimize
efficiency without adversely affecting the operating
characteristics of the core engine unit. A further objective of the
variable fan blades has been to achieve reverse thrust by giving
the fan blade contours a negative pitch.
The construction of apparatus for varying the fan blades has
nevertheless given considerable trouble from the design aspect in
that the variable outer row of rotor blades of an axial-flow fan
normally forms an integral part of the basic engine unit,
particularly so in constructions where the variable outer fan
blades and an inner row of rotor blades of a compressor of the
basic engine are mounted on a single rotor wheel.
According to the teaching of a French Pat. No. 2,046,297, the fan
rotor blades of a turbojet engine are made variable by means of a
complex planetary gearset within a central body arranged
immediately aft of the hub of the compressor of the basic engine
unit, where at least one tower shaft extends from the planetary
gearset and through the primary flow duct of said compressor to
transmit the actuating movement of the gearset to the fan blades
via further gearsets disposed in the space intervening between the
primary duct and the secondary duct. Apart from the complexity of
construction as a result of the particular arrangement of the
actuating gear and of the plurality of intermediate drives between
the variable fan rotor blades this arrangement exhibits a further
disadvantage in that uniform and direct transmission of the
necessary actuating moment to the fan blades is not adequately
ensured.
The present invention contemplates providing improved apparatus for
adjusting the fan rotor blades of a rotor wheel of the type having
different rows of blades along a radial stacking line, especially
for use with turbojet engines of multiflow construction, such that
direct transfer of the actuating force from the drive system to the
fan blades is ensured in a relatively uncomplicated fashion.
Additionally, the apparatus enables uniform transfer of the
actuating moment to be achieved in all selectable positions of the
fan blades. The drive system and the actuating system of said
apparatus furthermore economize space both by construction and
arrangement.
The present invention more particularly contemplates arranging the
apparatus for adjusting the fan blades between a primary flow duct
extending coaxially to the rotor wheel axis and a secondary flow
duct, and to provide said apparatus with a bearing arranged
coaxially to the rotor wheel axis for axial sliding movement within
fixed recesses in a fixed engine casing, where the blade actuating
force is transmitted to the outer bearing race of said bearing
while the inner race of said bearing is connected with an annular
member which is arranged coaxially to the rotor wheel axis and is
coupled with blade stems of pivotally mounted fan rotor blades via
actuating levers.
The present invention provides an advantage over previously
disclosed solutions in that it permits the necessary blade
actuating force to be transmitted directly and in a surprisingly
simple fashion from a fixedly mounted actuating means
(hydraulically or pneumatically operated actuating cylinders) to
the fan blades through the operably rotating rotor wheel.
These and further objects, features and advantages of the present
invention will become more obvious from the following description
when taken in connection with the accompanying drawings which show,
for purposes of illustration only, a single embodiment in
accordance with the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a partial longitudinal sectional view which substantially
illustrates a preferred embodiment of the present invention;
FIG. 2 is a partial front view taken along line II--II of FIG. 1
which illustrates details of a pair of variable fan blades arranged
on a rotor wheel in accordance with FIG. 1, with parts broken away
for clarity; and
FIG. 3 is a partial top schematic view (horizontal development of a
view taken in direction of arrow III of FIG. 1) which illustrates
details of the apparatus of this invention on a portion of a rotor
wheel.
DETAILED DESCRIPTION OF THE DRAWINGS
FIG. 1 illustrates a portion of a rotor wheel 1 for use in a
turbojet engine of multiflow construction. The rotor wheel 1
exhibits an inner row of compressor rotor blades 2 which are
arranged coaxially to the longitudinal axis A of the rotor wheel
and which discharge compressed air into a primary flow duct 3 of
the core engine unit. The rotor wheel 1 is externally provided with
a plurality of circumferentially equally spaced variable fan blades
4 which discharge compressed air into a secondary flow duct 5 which
extends coaxially to the produced axis of the rotor wheel or
longitudinal centerline of the engine. Since details of the
remainder of a turbojet engine with which the present disclosure is
associated will be readily understood by one skilled in the art,
given the present invention, such details have not been included
herein in order not to obscure the invention. In this connection,
the air passing through flow duct 3 will serve as combustion air
for a combustion chamber arranged downstream thereof, and jet
exhaust nozzle means and/or propellor rotor means as well as
turbine means to drive the rotor wheel will be powered by exhaust
gases from the combustion chamber.
Reference numeral 6 generally indicates the bearing and retaining
provisions for the fan blades 4.
The apparatus for varying the fan blades 4 is arranged within an
annulus 7 formed between the primary flow duct 3 and the secondary
flow duct 5.
The apparatus includes a plurality of equally circumferentially
spaced actuating cylinders 8 which are arranged concentrically to
axis A within the annulus 7 and which contain hydraulically or
pneumatically operated actuating pistons for sliding movement
relative to the cylinders 8.
The actuating cylinders 8 are attached to a fixed portion 9 of the
engine casing.
It is also contemplated by the present invention to utilize
electromagnetically operable means (e.g. solenoids) of conventional
design in place of the actuating cylinders and pistons.
Connected to the actuating pistons and extending from the actuating
cylinders 8 are piston rods 10 which connect, through ring elements
11, 12 and 13, to outer race 14 of a bearing 15 (antifriction
bearing) which extends coaxially to the production of the rotor
wheel axis or longitudinal centerline A of the engine.
A further ring element, 16, is fixedly connected with portion 9 of
the casing and envelopes with its axially directed portions 17, 18
a portion 18' of ring 12 on the one side and inner race 19 of the
bearing 15 on the other. A portion 20 of the ring element 16
further provides axially directed ways or guide slots 21 for
engagement with teeth 21' on the ring element 13 which is connected
with the outer race 14 of the bearing 15.
With this arrangement, the bearing 15 is flexibly radially
supported and recesses 22, 23 are formed in the casing to permit
the bearing 15 to slide axially.
For transmission of the force needed for varying the fan blades 4
from the bearing 15 via the rotor wheel 1 which rotates when the
jet engine is in operation, the inner bearing race 19 which
invariably rotates together with the rotor wheel is connected with
an annular member 24 which extends coaxially to the axis A of the
rotor wheel. Blade adjusting forces are transmitted from rod 10 to
inner race 19 by way of member 13 axially moving outer race 14 with
consequent axial movement of inner race 19.
With reference now to FIG. 3 which illustrates the apparatus of the
present invention in horizontal development, the annular member 24
exhibits equally spaced protuberances 25 which connect to actuating
levers 27 (FIG. 2) of the fan blades 4 via articulated bearings
26.
Using contours drawn in solid and dash-dotted line, FIG. 3 further
illustrates two different positions of the fan blades 4 as a result
of an actuating movement of the annular member 24 from left to
right accompanied by an analogous change in the position of the
protuberances 25. (Right most position of member 24, and
corresponding position of blades 4, depicted in dash-dotted lines
and left most position depicted in solid lines.) In FIG. 3, each of
the sets of piston-cylinder arrangements and associated linking
structure to annular member 24 are shown in schematic form as
control apparatus C, with two such control apparatus C being
depicted to indicate a plurality of same equally circumferentially
spaced about axis A.
As best illustrated in FIG. 1, the fan blades 4 are each radially
supported by their stem 28 within an annular bearing support 29.
For axial support and absorption of the centrifugal forces acting
on the blades during rotation of the rotor wheel 1, use is made of
a needle bearing 31 arranged between a rotationally symmetrical
step 30 on the respective blade stem 28 and the bearing support 29.
Radially inward extensions 29A of support 29 are connected to
extensions 2A of compressor rotor blades 2 by pins 40.
The above-described apparatus of the present invention is also
contemplated for use with jet engine configurations where the
respective longitudinal centerline of a fan rotor wheel does not
coincide with the longitudinal centerline of the core engine
unit.
The apparatus of the present invention may also be used in
conjunction with a rotor wheel which serves the function of an aft
fan of a jet engine, said rotor wheel conceivably being provided
with an inner row of turbine rotor blades arranged concentrically
to the axis of the rotor wheel and being driven by the gas flow
from the core engine unit.
It is furthermore contemplated by this invention that the apparatus
of this invention be used for axial-flow fan rotors of lift engines
in pancake construction.
Although the most preferred embodiments relate to turbojet engines,
the present invention also contemplates utilization of the
apparatus for adjusting fan blades in other fluid flow machines
having a single rotor wheel with two sets of blades supplying two
separate ducts and with at least one set of the blades being
adjustable.
While I have shown and described several embodiments in accordance
with the present invention, it is understood that the same is
susceptible of numerous changes and modifications as known to those
skilled in the art and I therefore do not wish to be limited to the
details shown and described herein but intend to cover all such
changes and modifications as are encompassed by the scope of the
appended claims.
* * * * *