вход по аккаунту


код для вставки
Jan. 14, 1947.
Filed July 23, 1943
2 Sheets-Sheet 1
Jm 14,
......... BE~RG
( ,
l W7
Patented .Fan. i4, 19%?
oat‘ stares
Carl Kt. eoderberg, Weston, Mass. assignor to
United Aircraft Corporation, East Hartford;
(Conn, a corporation of Delaware
Application July 23, 1963, Serial No. 495,92d
~2 Ciaims. (Ci. 253--39)
This invention relates to a blade mounting.
stress discs extending perpendicular to the ams
In mounting of turbine blades to resist the
of the rotor.
centrifugal forces resulting from high rotational
speeds, various interconnections have been used
The angle of convergence of the surfaces it
and it on the discs is such that the intersection
v between the blade root and the peripheries of the 5 of a line 132 at right angle to either surface and‘
rotary disc to’ which the blades are attached.
These mountings, however, have been construct-
midway between opposite edges of those surfaces,
and a line to at right angle to surface 3i‘! or 32
ed generally without consideration of the weight
and also midway between its edges, will be in ‘a
of the rotor. A feature of this invention is a
plane 46 which is substantially midway between
blade mounting which will hold the blade in place 10 opposite side walls of one of the supporting discs
in the rotor with a minimum of weight in both
blade root and rotor.
III or ‘I2. In this way the load on the discs re
sulting from the centrifugal force on the blade,
Blade mountings using a T-shape root section
represented by arrow A, is entirely a radial load
for the blade have been made in which the Tand is uniformly distributed across the entire
shape root has parallel surfaces engaging with 15 thickness of the discs.’ Atrows‘B, C and D on
cooperating cylindrical surfaces on the rotor.
lines 42, 44 and 46 show the directions: of the
Such an arrangement may cause parts of the
loads on the disc from which ‘it can be seen that
root section of the blade and the cooperating
there is no bending moment on the disc (except
parts of the rotor to be overstressed. With that
at its extreme outer end)
in mind, another feature of this invention is a 20
In the force diagram of Fig.3. the dimensions
blade mounting in which the load is substantially
of the forces 011 the blade root and the (11505 are
uniformly distributed, thereby making possible a
shown, and tho balancing of these forces‘ So that
substantial reduction ' in the dimensions of the
radial forces only are applied to the discs 15 made
Other objects and advantages will be apparent 25 Except‘ for the above-described cooperating
from the speci?cation and claims and from the
surfaces, the blade root is free from engagement
accompanying drawings which illustrates an embodiment of the invention,
Fig. 1 is a sectional view through a section of
with the discs- The blade root is thus hold in
contact with the discs by spaced cooperating ra
dial Surfaces and Spaced cooperating converging
the turbine rotor.
3') surfaces arranged to apply a uniformly distrib
Fig. an a view on a. larger scale to show the
uted load on the discs. The cooperating cylin
blade mounting.
drical surfaces hold the other cooperating sur
Fig. 3 is a force diagram.
faces in engagement.
The rotor 8 has a pair of opposed discs in and
. It is to be understood that the invention is .
l2, supporting a row of turbine blades 14 at; their 35 not limited to the speci?c embodiment herein il
peripheries. The rotor may have a, number of
lustrated and described, but may be used in other
axially spaced rows of blades alternating with
Ways Without departure from its spil‘it as de?ned
rows of vanes on a turbine casing surrounding
the rotor.
by the following Claims.
I claim:
Discs m and I2 have opposed converging sur- 4°
1- In a blade mounting in which a T-shaped
faces 16 and I8, Fig. 2, facing toward each other
root is positioned between Opposed annular
?anges on a support, the combination with ‘
engagement, with cooperating shoulders
forming converging surfaces 20 and 22 on root 24
spaced ?anges on Said root having radial 5111'‘
of blade l4. Surfaces l6 and i8 and also
sur- ‘ 4,)- sai
M935 roo
ng tomer
owar 51nd
an gppossd
con erg
ng owar
{323120 and 22 converge toward the up of the
Discs [0 and I2 also have peripheral ?anges 26
‘the tip of the blade, of cooperating radial sur
faces on the supporting ?anges facing away from
each other and engaging withthe radial surfaces
in the blade root, and cooperating shoulders on
and 28, the outer side surfaces of which are ra
dial to cooperate with the inner radial surfaces 50 the ?anges facing toward and diverging toward
30 and 32 of inwardly extending ?anges 34 and 36
the axis of the ?anges for'engagement with the
on the blade root.
The inner surfaces 38 and
40 on the flanges on the blade root may engage
Shoulders on the root, the angularity of the '
shoulders being such that the line of thrust on
corresponding oylmdl‘loal Surfaces on (11805 In
the diverging surface on each disc intersecting
and 12. The discs are both essentially constant- 55 the line of thrust on the radial surface at a point
substantially in a radial plane centrally of the
. The combination withi'a blade root having
opposed shoulders facing toward and converging
the rotor and diverging toward the axis to engage
with the shoulders on the blade root, said discs
also having substantially radial surfaces facing
awayqfrom each other and engaging the sub
toward the tip of the blade, and substantially ra $1 stantially radial surfaces on the blade root, the
angularity of the shoulders being such that the
dial surfaces facing each other and located be
line of thrust on each shoulder intersects the line
tween said shoulders and the blade tip, of a blade
- mounting including spaced discs forming a part
of thrust on each radial surface at a point sub
stantially in a radial plane centrally of the disc.
of a rotor, the inner surfaces of said discs hav=
‘ ins opposed shoulders facing toward the ants of no
Без категории
Размер файла
250 Кб
Пожаловаться на содержимое документа