U.S. patent number 3,806,274 [Application Number 05/282,778] was granted by the patent office on 1974-04-23 for gas turbine engine blades.
This patent grant is currently assigned to Rolls-Royce (1971) Limited. Invention is credited to Alan Moore.
United States Patent |
3,806,274 |
Moore |
April 23, 1974 |
GAS TURBINE ENGINE BLADES
Abstract
A gas turbine blade has a hollow interior space which is divided
to form flow passages for cooling medium. The flow passages are
bounded by the sides of a sheet-like insert the two blade walls,
and fins between the insert and the blade walls; they commence at
one end of the blade and extend in a spiral-like path around the
opposite sides of the insert.
Inventors: |
Moore; Alan (Bristol,
EN) |
Assignee: |
Rolls-Royce (1971) Limited
(London, EN)
|
Family
ID: |
26264234 |
Appl.
No.: |
05/282,778 |
Filed: |
August 22, 1972 |
Foreign Application Priority Data
|
|
|
|
|
Aug 25, 1971 [GB] |
|
|
39778/71 |
Aug 25, 1971 [GB] |
|
|
39778/71 |
|
Current U.S.
Class: |
416/97R;
416/96A |
Current CPC
Class: |
F01D
5/188 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/96-97,92 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Stevens, Davis, Miller &
Mosher
Claims
What is claimed is:
1. A gas turbine blade having opposed walls defining therebetween a
hollow interior space, an insert within said space, said insert
being formed of a solid sheet curved to the chamber of the blade,
and fins carried by said blade and extending between said insert
and said blade walls, said walls, said insert and said fins
defining in combination a plurality of flow passages for cooling
fluid, each said flow passage commencing at one end of the blade
and extending in a spiral-like manner around and along the
insert.
2. A blade as claimed in claim 1, which includes a plurality of
discrete pimples extending between the sides of the insert and the
blade walls within the flow passages for providing location for the
insert.
3. A blade as claimed in claim 2, wherein the fins and pimples are
formed integrally with the blade walls.
4. A blade as claimed in claim 1, wherein holes are formed in the
region of the leading edge of the blade for allowing cooling fluid
to pass to the exterior of the blade from the flow passages.
5. A blade as claimed in claim 1, wherein holes are formed in the
region of the trailing edge of the blade for allowing cooling fluid
to pass to the exterior of the blade from the flow passages.
6. A blade as claimed in claim 1, wherein the insert has a root end
portion at which it is secured within the blade by brazing, the
insert being otherwise unattached to allow for differential
expansion.
7. A blade as claimed in claim 1, wherein at least some of the flow
passages are arranged for individually serving one edge only of the
blade.
8. A gas turbine rotor having a plurality of blades as claimed in
claim 1, arranged for supply with cooling fluid at their root
ends.
9. A gas turbine rotor according to claim 8, which includes a
shroud connecting together the outer ends of the blades, the
arrangement being such that cooling fluid may pass from said flow
passages into cooling relation with the shroud.
10. A rotor according to claim 9, wherein the radially inner
surface of the shroud is formed with channels, and the blade walls
are formed with holes arranged for directing cooling fluid from the
flow passages along the channels.
11. A blade as claimed in claim 6, wherein said fins are terminated
immediately adjacent said root end portion of said insert.
12. A gas turbine blade having opposed walls defining therebetween
a hollow interior space, and an insert within said space, said
insert being formed of a solid sheet curved to the chamber of the
blade and connected to said walls by brazing at the root end of the
blade, being otherwise unattached to allow for differential
expansion, said walls being integrally formed with fins extending
between said insert and said blade walls, said walls, said insert
and said fins defining in combination a plurality of flow passages
for cooling fluid to flow through the blade commencing at the root
end of the blade and passing in a spiral-like manner around and
along the insert.
Description
This invention relates to the blading of gas turbine engines, and
although not so limited, has particular reference to rotor blades
for such engines.
As is known, it is advantageous to provide for the cooling of gas
turbine rotor blades, and many different ways of doing this are
known. In particular, it is known to provide a cooling air flow
through the interior of the blade, and the cooling is the more
effective, the greater the volume of air flow and the greater the
velocity of the air as it passes through the blade.
In very small rotor blades, e.g., less than 11/2 inches long
considerable difficulties are encountered in providing flow
channels by means of which satisfactory cooling can be achieved.
The present invention aims to provide a rotor or stator blade
construction which enables improved cooling to be obtained.
An object of the invention is to provide an improved a gas-turbine
blade with a hollow interior space which is divided to form flow
passages bounded by the sides of a sheet-like insert, the two blade
walls and fins between the insert and the blade walls, the flow
passages commencing at one end of the blade and extending in a
spiral-like path around and along the insert.
In a preferred form, the invention is applied to rotor blades which
are fed from the root end.
The invention will now be described with reference to the
accompanying drawing, in which:
FIG. 1 shows a sectional elevation of a gas turbine rotor blade
according to the invention, the section being taken on the line
B--B in FIG. 2;
FIG. 2 shows a section on the line A--A in FIG. 1, to a scale 10
times that of FIG. 1; and
FIG. 3 shows an isometric view of the shroud end of the rotor
blade, seen looking from the root towards the shroud.
The rotor blade in FIG. 1 has leading and trailing edges 10, 11, a
shroud end 12 and a root end 13. The blade is hollow, and the space
within it is effectively divided into two by means of a sheet-metal
insert 14 which extends substantially the full radial length of the
blade being brazed to the blade at its root end but otherwise
unattached to allow for differential expansion. The arrangement of
the insert 14 within the blade is clearly seen in FIG. 2.
It will be seen that the insert is located between a large number
of pimples 15 (indicated in FIG. 1 by small crosses) and by a
series of helical fins 16. The blade is conveniently made with the
pimples and fins cast onto the interior surfaces of the blade walls
17, 18. The insert 14 stops short of both the leading and trailing
edges of the blade, thus leaving spaces around which air may pass
in order to progress from one side of the insert to the other.
Referring now again to FIG. 1, it will be seen that air supplied to
the interior of the blade from the root end 13 can enter any one of
a series of flow passages extending obliquely up one side of the
insert passing round the leading or trailing edge of the insert,
and then continuing obliquely up the other side of the insert. An
arrow traces one possible path. As it progresses radially outwards,
a proportion of the air is allowed to escape through leading edge
film cooling holes 20, and through trailing edge slots 21. Since
the volume of air flowing through the blade is thus diminished, the
flow passages are designed to be of smaller cross section towards
the outer shroud end 12 of the blade. This can be achieved by
arranging that the spacing of the fins 16 is reduced or, more
conveniently, by reducing the width of the passages. This maintains
the airflow velocity substantially constant. In addition, the
velocity of the air flow may be varied by altering the angle at
which the fins 16 are cast onto the interior surfaces of the
blade.
In a preferred form of the invention, holes 22 (FIG. 3) may be
provided for the final escape of the cooling air in the angle
formed by the blade proper wall 17 and the shroud 23. The air thus
released can be used to cool the shroud by causing it to spread
over the shroud 23 along channels 24 formed in the radially inner
surface thereof.
It will be seen that a blade constructed in the fashion described
is relatively easy to produce, particularly since the insert is
solid and therefore easy both to manufacture and to insert into the
blade, while the blade itself can be conveniently cast, together
with, fins and pimples, using only a single piece core.
If desired, in the described arrangement the holes 20 and/or the
holes 21 and/or the pimples 15 may be omitted, the cooling medium
may be liquid or a gas other than air, and the fins 16 and pimples
(if provided) may be other than integral with the blade walls.
In a further variation of the described arrangement at least some
of the flow passages for cooling air are such that they
individually serve either the leading edge of the blade or the
trailing edge of the blade, but not both. This may be effected by
suitable choice of the inclination of the fins 16. Such an
arrangement may enable different supplies to be used for the
leading and trailing edges of the blade to make allowance for the
different ambient air pressures existing in those regions.
* * * * *