U.S. patent number 3,876,330 [Application Number 05/352,705] was granted by the patent office on 1975-04-08 for rotor blades for fluid flow machines.
This patent grant is currently assigned to Rolls-Royce (1971) Limited. Invention is credited to Harry Pearson, Lawrence John Williams.
United States Patent |
3,876,330 |
Pearson , et al. |
April 8, 1975 |
ROTOR BLADES FOR FLUID FLOW MACHINES
Abstract
This invention has the object of improving the efficiency of
fluid flow machines generally, and particularly the specific fuel
consumption of gas turbine engines. The invention comprises a
fluid-flow deflector member for a rotor blade, which projects
outwardly from the radially outer end of the blade into the region
of leakage fluid flow in the clearance between the machine casing
and the blade. The fluid-deflector member has a fluid-deflecting
surface which is oriented generally transversely of the direction
of blade rotation and which faces the upstream direction. An
exchange of momentum occurs between the flow of leakage fluid and
the deflector surface, and the deflector member thus transmits a
force to the blade acting in the direction of blade rotation. If
desired, the deflector member can also be positioned to extract
momentum from blade cooling fluid ejected from the radially outer
end of the blade, thus further augmenting rotor torque and
increasing machine efficiency.
Inventors: |
Pearson; Harry (Turnditch,
EN), Williams; Lawrence John (Castle Donington,
EN) |
Assignee: |
Rolls-Royce (1971) Limited
(London, EN)
|
Family
ID: |
10113289 |
Appl.
No.: |
05/352,705 |
Filed: |
April 19, 1973 |
Foreign Application Priority Data
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Apr 20, 1972 [GB] |
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18488/72 |
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Current U.S.
Class: |
416/92; 415/115;
415/116; 415/173.6; 416/96A; 416/96R; 416/97A; 416/97R; 416/189;
416/192; 416/193R |
Current CPC
Class: |
F01D
5/20 (20130101); F01D 5/18 (20130101); F01D
5/225 (20130101); F05D 2240/81 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 5/14 (20060101); F01D
5/20 (20060101); F01d 005/18 () |
Field of
Search: |
;416/190,191,193,221,92,97,192 ;415/172 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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989,260 |
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Apr 1965 |
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GB |
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521,551 |
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Mar 1965 |
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IT |
|
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Cushman, Darby & Cushman
Claims
What we claim is:
1. An axial flow turbine rotor blade having a shroud at its
radially outer end and a fluid deflecting member projecting
outwardly of the radially outer suface of said shroud into the
region of leakage fluid flow between the high and low pressure
sides of the shroud, said fluid deflecting member possessing a
substantially fin-shaped fluid-deflecting surface which over at
least the greater part of its area is oriented transversely of the
direction of rotation of said blade, but not normal thereto, and
faces towards both the high pressure side of the shroud and the
trailing edge of the shroud, thereby to deflect at least a portion
of said leakage flow and exchange momentum therewith, a force
acting in the direction of blade rotation thereby being produced on
said member to assist the rotation of said blade.
2. An axial flow turbine rotor blade having a shroud at its
radially outer end and a fluid deflecting member projecting
outwardly of the radially outer surface of said shroud into the
region of leakage fluid flow between the high and low pressure
sides of the shroud, said fluid deflecting member possessing a
substantially fin-shaped fluid-deflecting surface which over at
least the greater part of its area is oriented transversely of the
direction of rotation of said blade, but not normal thereto, and
faces towards both the high pressure side of the shroud and the
trailing edge of the shroud, thereby to deflect at least a portion
of said leakage flow and exchange momentum therewith, said rotor
blade being adapted to be fluid-cooled, the cooling fluid being
discharged from one or more apertures in the radially outer side of
said shroud, at least a portion of said cooling fluid being
deflected by the fin-shaped member to exchange momentum therewith,
a force acting in the direction of blade rotation being thereby
produced on said fin-shaped member to assist the rotation of said
blade.
3. An axial flow turbine rotor blade having a shroud at its
radially outer end and a fluid deflecting member projecting
outwardly of the radially outer surface of said shroud into the
region of leakage fluid flow between the high and low pressure
sides of the shroud, said fluid deflecting member possessing a
substantially fin-shaped fluid-deflecting surface which over at
least the greater part of its area is oriented transversely of the
direction of rotation of said blade, but not normal thereto, and
faces towards both the high pressure side of the shroud and the
trailing edge of the shroud, to thereby deflect at least a portion
of said leakage flow and exchange momentum therewith, said rotor
blade being fluid-cooled, the cooling fluid being discharged from
apertures in the radially outer side of said shroud, at least one
of said apertures being covered by a hollow cap member which is
adapted to deflect said cooling fluid through one or more further
apertures in said cap in a direction substantially opposite to the
direction of rotation of said blade to assist therewith, the
fin-shaped member being on the radially outer surface of said cap
and projecting outwardly therefrom, said leakage fluid and said
cooling fluid generating a force acting in the direction of blade
rotation to assist the rotation of said blade.
4. An axial flow turbine rotor blade having a shroud about its
radially outer end and a fluid deflecting member projecting
outwardly of the radially outer surface of said shroud into the
region of leakage fluid flow between the high and low pressure
sides of the shroud, said fluid deflecting member possessing a
substantially fin-shaped fluid-deflecting surface which over at
least the greater part of its area is oriented transversely of the
direction of rotation of said blade, but not normal thereto, and
faces towards both the high pressure side of the shroud and the
trailing edge of the shroud, to thereby deflect at least a portion
of said leakage flow and exchange momentum therewith, said turbine
rotor blade being adapted to be fluid-cooled, the cooling fluid
being discharged from apertures in the radially outer side of said
shroud, at least one of said apertures being covered by a hollow
cap member which is adapted to deflect said cooling fluid through
at least one further aperture in said cap onto the fluid-flow
deflecting surface of the fin-shaped member which projects
outwardly from the radially outer surface of the shroud into the
region of fluid-flow over said radially outer surface, a force
being thereby produced which acts in the direction of blade
rotation on said member to assist the rotation of said blade.
5. An axial flow turbine rotor blade according to claim 1 in which
the fin-shaped member is of substantially triangular configuration
and has its greatest height relative to the radially outer shroud
surface at the position of greatest momentum of the flow of fluid
over said surface.
6. An axial flow turbine rotor blade according to claim 1 in which
the radially outer edge of said fin-shaped member is of
substantially uniform height relative to the radially outer shroud
surface.
7. An axial flow turbine rotor blade according to claim 1 in which
the fluid-deflecting face of the fin-shaped member makes an acute
angle with the radially outer shroud surface.
8. An axial flow turbine rotor blade according to claim 1 in which
the radially outer free end of said fin-shaped member is of arcuate
shape and overhangs the fluid-deflecting face of the fin-shaped
member.
9. An axial flow turbine rotor blade according to claim 2 in which
the fluid deflecting surface of the fin-shaped member is concave in
the same sense as the blade aerofoil portion.
10. An axial flow turbine rotor blade according to claim 1, said
blade being a gas turbine engine turbine rotor blade.
11. An axial flow turbine rotor blade according to claim 2 in which
the cooling fluid is air.
Description
This invention relates to means whereby the efficiency of fluid
flow machines may be increased. In particular, the invention
provides means whereby flow through and past shrouded turbine
blades of a gas turbine engine may be more efficiently
utilised.
Turbine blades in many modern gas turbines have flange portions at
their radially outward ends which co-operate with those of other
blades which are circumferentially and axially spaced from them to
define, or partially define, a radially outer wall of the annular
gas duct through which the major portion of the combustion gases
flow towards the exhaust nozzle. These flange portions are normally
referred to as forming the "shroud" of the blade, and where the
term "shroud" is used in this specification it will carry the above
meaning.
In modern gas turbine engines utilising high temperatures of
combustion, large quantities of relatively cool air may be passed
through passages or the like in at least the first stage turbine
blades of the turbine in order to keep the aerofoil walls of the
blades at temperatures compatible with required blade strength and
integrity. Prior to the present invention it has often been the
case that cooling air has been allowed merely to issue radially
outwards from the end of the blade and flow over the radially outer
surface of the shroud. This is wasteful when one considers that
work has been done in pressurising the cooling air to force it
through the blades, and that therefore it posesses momentum due to
its velocity as it passes out of the blade.
It is thus one object of the present invention to provide means
whereby the cooling air may be utilised after it has emerged from
the radially outward end of the blade such that at least some of
the momentum of the cooling air is transferred to the blade thereby
producing a force on the blade acting in the direction of blade
rotation.
It will be seen that the efficiency of the turbine will be
increased relative to a turbine having blades which do not have
such means because the additional force acting in the direction of
blade rotation will allow lower fuel consumption to be achieved for
a given speed of rotation.
It is also a characteristic of shrouded gas turbine rotors that
leakage flow of gases occurs between high and low pressure sides of
the shroud via the space between the radially outer surface of the
shroud and the wall of the fluid flow duct containing it. Where the
term "leakage flow" is used in this specification, it will carry
the above meaning. This leakage flow reduces the efficiency of the
turbine, and it is therefore an object of this invention to utilise
said flow so that at least some of the momentum of said flow will
be transferred to the shroud in such a way as to produce forces on
the rotor acting in the direction of rotation.
According to the present invention an axial flow turbine rotor
blade having a shroud at its radially outer end has fluid flow
deflecting means comprising at least one fluid-deflecting surface
projecting from the radially outer end of said shroud into the
region of leakage fluid flow over the radially outer end of said
shroud, characterised in that said fluid-deflecting surface over at
least the greater part of its length is oriented transversely of,
but not normal to, the direction of rotation of said blade, such
that said deflecting means transmits a force to said blade acting
in the direction of rotation of said blade to assist the rotation
thereof, said force resulting from an exchange of momentum between
said leakage fluid flow and said fluid-deflecting surface.
The turbine rotor blades may be fluid-cooled such that in operation
they discharge cooling fluid from one or more apertures in the
radially outer surface of said shroud at the end of the blade, the
fluid-flow deflecting surface being positioned to deflect said
cooling fluid in addition to the leakage air, thereby to exchange
momentum with said cooling fluid to produce a force on said
deflecting means acting in the direction of blade rotation to
assist therewith.
In another embodiment of the invention, one or more the cooling
fluid-discharging apertures in the radially outer surface of the
shroud may be covered by a hollow cap member which is adapted to
deflect said cooling fluid through one or more apertures in said
cap in a direction substantially opposite to the direction of
rotation of said shroud to assist therewith, the fluid deflecting
surface of said fluid deflecting means being situated on the
radially outer side of said hollow cap member to deflect the
leakage fluid flow.
In an alternative arrangement the hollow cap member is adapted to
deflect the cooling fluid through one or more apertures in said cap
member onto the fluid flow deflecting surface, which in this case
is situated downstream of the cap member.
The rotor blade may be either shrouded or unshrouded at its
radially outer end, and in the case of an unshrouded blade, it is
preferred that the fluid flow deflecting surface is the concave
face of a lip which extends along the convex side of the aerofoil
at the radially outer end thereof and which projects therefrom into
the region of fluid flow over the blade tip.
The axial flow turbine is preferably part of a gas turbine engine,
the rotor blade being a gas turbine rotor blade. The cooling fluid
is preferably air, but may be water, steam, or a mixture of water
or steam with air.
The fluid flow deflecting means may be formed as a separate
component and thereafter brazed, welded or otherwise fixed to the
shroud. Alternatively, it may be formed as an integral part of the
blade shroud or may form part of or be attached to a cap-like
component which in turn may be fixed to the shroud. Said cap-like
component may also incorporate flange-like members adapted to
produce a seal between said component and the wall of the fluid
flow duct.
If the deflection means is formed as a separate component, it
preferably comprises the fluid-deflecting portion and a
base-portion by which said deflecting portion is fixed to the
shroud or to the cap-like component, but if said deflection means
is formed integrally with said shroud or said cap-like component,
said deflection means may comprise only said fluid deflecting
portion.
Specific embodiments of the invention will now be described by way
of example only and with reference to the accompanying drawings in
which
FIG. 1 is a diagrammatic representation of a gas turbine engine
which may incorporate the present invention.
FIG. 2 is a perspective view of a first-stage turbine blade which
does not incorporate the present invention.
FIG. 3 shows a blade according to the invention as it could be
situated in an engine according to FIG. 1.
FIG. 4a is an enlarged scrap view of the blade shroud as shown in
FIG. 3.
FIG. 4b is a view of the shroud as seen on arrow B in FIG. 4a,
and
FIG. 4c is a representation of the view on section C--C in FIG.
4b.
FIG. 5a is a partly sectioned side elevation of the tip of a
shrouded turbine blade showing a further embodiment of the
invention.
FIG. 5b is a view of the top of the turbine blade shroud portion as
seen from the direction of arrow B'.
Referring to FIGS. 1 and 3, a ducted fan gas turbine engine 1
comprises a fan section 3, compressor section 5, combustion
apparatus 7, turbine section 9 and exhaust section 11, these all
being arranged in flow series with respect to each other.
As illustrated in FIG. 1, the turbine 9 comprises several stages,
the first stage of which may include the turbine blade indicated by
reference numeral 13 as shown in FIG. 3. This blade 13 receives
combustion products from annular combustion chamber 15 via a
plurality of nozzle guide vanes 17 as it rotates about the axis of
the engine.
As is best seen from FIG. 2, a typical turbine blade 12 of the
prior art comprises an aerofoil-shaped portion 19, a root-portion
21 whereby the blade is retained in a turbine disc such as that
shown in FIG. 3 by the reference numeral 14, a platform portion 23
with sealing flanges 24, and a shroud portion 25 having sealing
flanges 26.
Cooling air is supplied to the blade at A, passes up through the
aerofoil portion 19 by means of a passage or passages (not shown)
and is expelled at E from holes (not shown, but similar to holes 34
in FIG. 4b) in the shroud 25.
FIG. 3 includes a blade 13, which is generally similar to blade 12
but which is modified according to the present invention. Those
parts which correspond to parts already identified in connection
with FIGS. 1 and 2 are numbered identically, and will require no
further description. As before, cooling air passes up the inside of
the blade in the direction indicated by the arrow C and exhausts
from the radially outer side of the shroud 25.
In some modern gas turbines, high mass flows of cooling air are
used because of the high temperature of the combustion gases which
impinge upon the blade. In the blade according to FIG. 2, the
residual energy of this high mass flow was wasted because the air
left the shroud in a radial direction and then merely flowed out
over the shroud surface, "sandwiched" between the shroud and the
turbine duct wall. However, in FIG. 3, a fin or fence-like member
27 is brazed or otherwise fixed onto the radially outer side of the
shroud 25 in order to intercept the cooling air as it flows out
over the shroud in the restricted space between the shroud and the
duct wall, and hence to produce a momentum interchange between the
cooling air and blade.
The shape and position of the member 27 as shown more clearly in
FIGS. 4a, b and c.
FIG. 4a is an enlarged section view of the shroud 25 and adjacent
parts shown in FIG. 3. It will be seen that the shroud 25 has two
pieces fixed thereto, these being a cap 29 having sealing flanges
26, and the member 27. Sealing flanges 26 operate in conjunction
with seal lining 30 which is attached to the inner casing 32. The
purpose of flanges 26 and lining 30 is to reduce the leakage flow
of air and combustion gases from the high pressure area H to the
lower pressure area L via the clearance between blade shroud 25 and
duct wall 32; obviously, the greater the proportion of gases which
pass over the aerofoil surface 19 and hence exchange momentum with
the blade, then the greater the efficiency of the turbine will be.
Lining 30 is abradable so that the flanges will cut channels for
themselves as the clearances vary according to engine operating
conditions. In spite of these precautions, however, a leakage flow
occurs, and another function of the fence is to intercept leakage
gases as they flow over the shroud and thereby transfer some of
their momentum to the blade in the direction of rotation.
The position of the member 27 on the shroud 25 in relation to the
cooling air exit holes 34 and the cap 29 is shown in FIG. 4 b,
which is a plan view of part of the shroud 25 as seen when looking
along arrow B is FIG. 4a. The direction of rotation of the blade is
indicated by arrow R, and it will be noticed that the fin or fence
(as shown by the unbroken lines) is in the form of a straight strip
which is fixed to the shroud 25 in a position flanking the holes 34
and transverse of the direction of rotation. If a cross-section of
the fence is taken on line C--C, the view in FIG. 4c is obtained,
and it will be seen that the section is substantially L-shaped as
shown by the unbroken lines. The base of the L may be secured to
the shroud by brazing or welding.
Returning to FIG. 4a, member 27 as shown by the unbroken lines has
a fence-portion of variable height along its length relative to the
shroud surface. The fence portion approximates a triangular shape,
the apex of the triangle being situated such that the greatest
fence area is presented to the region of greatest combined cooling
air and leakage gas flow. Abradable seal-lining 30 conforms
approximately to the shape of the fence portion but is obviously
spaced therefrom as shown.
Alternative embodiments of the invention are shown in FIGS. 4a, b
and c means of broken lines. In FIG. 4a, the member 27 is modified
to have a fence portion of constant height over the major portion
of its length, as shown by the broken line. As a result, the
profile of the seal lining 30 is also modified to that shown by the
corresponding broken line. Such a profile would be used for ease of
manufacture and/or in cases where the combined fluid flow across
the shroud is substantially constant all along the shroud
width.
Another alternative embodiment is shown by the broken lines in FIG.
4b, where reference numeral 27b indicates a member in which the
fence portion when seen in plan view is arcuately disposed
alongside the cooling air holes in contrast to the previously
described member 27 shown by unbroken lines, which is linearly so
disposed. The arcuately formed embodiment may be more efficient in
collecting the cooling air as it spills over the shroud.
yet two more embodiments are shown by the broken lines in FIG. 4c.
As previously mentioned, the unbroken lines in FIG. 4c define a
cross-section of the member 27 taken on section line C--C in FIG.
4b, in which the gas-intercepting surface of the member is disposed
normal to the shroud surface. However, greater efficiency may be
obtained by employing a fence-portion the top part of which is
inclined (36) or curved (38) over towards the cooling air exit
holes in the shroud. In this way, more efficient use of the air may
be made before it spills over the top of the fence.
It should be realised that the unbroken lines in FIGS. 4a, b and c
illustrate one basic embodiment seen in three different views, but
that the broken lines in the same Figures respectively illustrate a
further four separate embodiments drawn in for comparison with the
corresponding view of the basic embodiment. However, features of
all five embodiments may easily be brought together in any
combination, and still further variations will be apparent to one
skilled in the gas turbine art.
As yet another example, the present invention may be used in
conjunction with the invention disclosed in our co-pending U.S.
Patent application Ser. No. 406,388, in which a shroud cap, which
could be similar to the one numbered 29 in FIG. 4 of the present
application, extends over cooling air exit holes in the blade
shroud and incorporates ducts or channels to deflect the cooling
air which exits from these holes. In an embodiment of the invention
of the co-pending application, the direction of discharge of
cooling air from the cap is approximately tangential to the rotor
and opposite to its direction of rotation. A deflector fence may in
this case be situated on the top of the cap to intercept leakage
air passing over the top of the cap.
An alternative way of using a deflector cap and fence in
conjunction is shown in FIGS. 6a and b of the present
specification. A blade 46 is provided with an array of cooling air
channels 48 in both leading and trailing edges, and corresponding
cooling air exit holes are provided in the radially outer side of
the shroud 50. A hollow shroud cap 52 (having sealing fins 26 as
described with reference to FIG. 4) is brazed or otherwise fixed in
position over the holes. The cooling air enters the space 54
between the shroud surface and the cap and is exhausted from the
cap in the direction of arrow F through the opening 56 at the
downstream end.
The deflector 58 is essentially of the same form as that described
in relation to the full lines of FIG. 4, except that a blanking
plate 60 with dust hole 62 is formed as an integral part of the
deflector fence to cover the cooling air exit hole 48' on the
downstream edge of the shroud. This has the effect of stopping most
of the air flow in the cooling air channel from escaping through
the shroud, thus ensuring a plentiful supply of air for
film-cooling of the trailing edge of the blade. The small dust-hole
is provided for the purpose of expelling any small particles which
would otherwise accumulate in the cooling air channel.
As can be seen from FIG. 5a, the direction F of discharge of
cooling air from the cap is such as to direct the air onto the
deflector fence, which also intercepts air issuing directly from
uncapped cooling air holes, as well as some leakage gas. The
provision of such a deflector cap, which collects cooling air
exhausted from the upstream edge of the shroud and directs it
towards the downstream edge to be intercepted by appropriately
oriented deflector fence, effectively increases the
fluid-collecting ability of the defelctor fence whilst preserving
an efficient orientation on the shroud.
Expected gains in the efficiency of a modern gas turbine engine
when fitted with deflector fences are worthwhile. For example,
specific fuel consumption may be improved by an amount of the order
of 1-2 percent.
* * * * *