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Патент USA US2411124

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Nov. 12, 1946.
2,411,124 .
Filed Jan. 13, 1944
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Patented Nov. 12, 1946
umrsosrnss PATENT OFFICE
Karl Baumann, Mere, Knutsi’ord, England, as
Signor to Metropolltan-Vickers Electrical Com
pany Limited, London, England, a company of ,
Great Britain
Application January 13, 1944, Serial No. 518,166
In Great Britain November 1, 1941
5 Claims. (01. 2304-116)
This invention relates to internal combustion
power plant for propulsion in air of the kind
wherein the energy in the rearwardly exhausting ‘
products of combustion is utilised at least to
assist in the propulsion by so-called jet action,
such plant being notably but not exclusively em
ployed for the propulsion of aircraft.
The invention furthermore speci?cally con
cerns an internal combustion power turbine com
ponent operated by the exhausting products of
combustion and arranged to drive or work upon
air additional to that used for the internal com
bustion, whereby essentially to increase the pro
pulsion effect in atleast one way. A
sion. Conveniently also at least oneand pref
erably each of the stages of the power turbine
blading is formed or provided with a. foundation
ring (and conveniently also with shrouding as
and where may be found necessary) again to pro-,
vide a self-supporting structure in the case of
each turbine stage.‘
In carrying out the invention according to a
feature thereof, a or the self-supporting air blad
lng structure or element may have the founda
tion ring of the inner blading periphery carried
from the corresponding rotor of the power tur
bine by means of a, thin axially extending or
cylindrical ?ange, 'preferablypalso with a con
The invention mainly but not exclusively con 15
necting portion or portions of re-entrant or an
cerns subsidiary features and structural details
nularly dished form, or by means of inner and
of, and also some improvements‘in, the contra
outer cylindrical portions united at one end by an
rotational “thrust augmentor” and plant in ac
integral annular portion which is itself of semi
cordance with copending application Serial No.
section or substantially so, these two co
518,165, ?led January 13, 1944, and is directed to 20 circular
axial cylindrical portions and the uniting portion
the convenient production of a plant of desirably
being hereinafter for brevity referred to as a
low Weight and small volume with provision for
“swan-neck” member or portion: the other ends
?exibility for differential thermal expansion.
In the following speci?cation for the sake of ‘ of these members are integral with or rigidly at
brevity, clearness and convenience of description, 25 tached respectively to the foundation ring of the
air blading stage and, within that, to the shroud
the subject matter of the invention will be re
ing or foundationv ring of the outer periphery of
ferred to broadly as applied to a thrust aug
a row of power turbine blading driving the air
mentor and the turbine forming an essential part
blading. In a, modi?cation of the former of the
thereof, preferably a low pressure turbine, will
mostly be referred to as the power turbine, whilst 30 two speci?c arrangements just above described
the cylindrical member may be articulated with
the air screws or ducted fan stages or low pres
‘ sure compressor driven by said power turbine will
respect to one or both of the rings with which it
be referred to mostly as air blading or ducted fan
connects, that is to say the connecting member
may comprise a relatively thin walled coaxial cyl
stages. Furthermore, for convenience and by
inder the two edges of which areformed or pro
bustion products driving the power turbine oi the 35 vided with enlargements of part circular cross
section engaged in correspondingly shaped an- >
thrust augmentor are those discharging from a
nular recesses in the foundation members which
“compressor” turbine, that is, another turbine
used wholly or mainly for driving the compressor
are thereby united. In another arrangement
which supplies air to a combustion chamber, the
each of the foundation members may be formed
gases leaving which pass through both of said
or provided with a, short axially extending ?ange,
the one overlapping the other, and the two con
According to the present invention at least one
nected together by tapered radial pins engaged in
air blading stage, and preferably each air blading
similarly tapered holes in both ?anges, the taper- \
stage, is mounted on a'foundation ring at the
45 ing converging to the axis of rotation; this ar—
base-or radially inner-end of‘ the blading row
rangement again providing for thermal expan
(such row also having if desired outer shroud
sion e?ects in per se known manner in steam tur
way of example it will be assumed that the com
~ ing), so as to form a self-supporting structure
bines, and previously proposed in other situations
which, or each of which, is carried by the or a
in internal combustion turbine plant.
rotor of the power turbine through the medium 50 Several arrangements in accordance with the
of an axially extending member or'members
invention and further'features thereof will now
which may assume various forms (some of which
be described with reference to the accompanying
are per se known) and which permit radial ?ex
drawings, in all the ?gures of which it can be
ibility between the members thereby connected,
assumed that there are two stages of air screws
for accommodating differential thermal expan 55 or
ducted fan blading and four stages of power‘
rotation principle. '
erably of tapering section such as illustrated in
Figs. 11 and 12.
. In the drawings like or similar reference nu
merals will be used for the same ‘parts, where
Preferably at leastone, and maybe two' or"
possible, in the several ?gures, all the ?gures of
three or four of the turbine blading stages are’
which are fragmentary views illustrating con
provided at their inner peripheries with founda
tion rings‘designated la, 2a, 3a and 4a, whilst,
as illustrated only in Fig. 9 there may alterna
ventionally in sectional elevation the upper halves
of the several arrangements.
In the drawings;
6 (only parts of which are shown in Figs. 1, 2, 3.‘
4, '7, '8 and 9) or by undished'radial discs, pref:
turbine blading, all operating-on the contra
' '
Fig. 1 is an axial section of the turbine and 10 tively be a common inner foundation ring such
as 3ala for the ?rst and third blading stages,
fan blading of a turbine structure embodying the
present invention.
or alternatively and similarly a common outer
foundationring for the second and fourth stages.
Certain of these turbine inner foundation rings,
or, in the case of Fig. 9, both of them, may be
Fig. 2 is a view similar to Fig.’ 1, but showing
a modi?ed construction of the shrouding of the
turbine blading and foundation rings of ‘stages
of the turbine blading.
Fig. 3 is a view similar to .Fig. l, but showing
inner foundation rings for all of the turbine stages
and a modi?cation of the outer shrouding thereof.
Fig. 4' is a view similar to the preceding ?g 20
ures but showing a modi?cation of the connec
tions between the turbine stages and the fan
integral with, but are preferably formed ‘sep
ar'ately from and rigidly connected with the discs
5 ‘and. 6 (Figs. l_to 10). On the other'hand, in
Figs. 11 and 12 the inner foundation rings indi
cated at lb and 2b in Fig. 11 form the rims of,
the radial undished discs 5a and 6a.
Thus in most of the ?gures of the drawings,
in general the two foundation ringsof the ducted
fan blading rows are designated Ia and Illa;
up and welded structure between the turbine 25 inner foundation rings of the power turbine blad- _
ing stages‘are indicated by la, 2a, 3a and 4a;
stages and the fan blading.
-outer foundation rings of the turbine blading
Fig. 6 is a detail axial section showing a riv-'
Fig. 5‘ is a fragmentary axial section of a built;
eted assembly connecting the bladings of the tur
bine and fan and providing for ?ow of cooling
are indicated similarly by-the suffix b. Inner
shrouding rings of the turbine blading stagesv l,
30 2, 3 and 4 are indicated by similar numerals
with the su?ix c and outer shrouding rings of
Fig. 7 is an axial section showing a tapered pin
such blading are'indicated by the suiilx d applied
arrangement for connecting the bladings of the
turbine and fan.
to the same numerals l, 2, 3 and 4.
Since the generally cylindrical structures of ‘
Fig. 8 is an axial section showing another
the herein called inner and outer rotors of the
modi?ed arrangement for connecting the turbine
turbine must be substantially rigid and the con
' and fan bladings.
Fig. 9 is an axial section showing dished discs
for mounting the turbine bladings and ventilating
holes for protecting the fan bladings from high
tinuity of the annular passage containing the
contra-rotational blading must be ensured, inner
turbine connecting sleeves are employed for the
Fig; 10 is an axial section showing the bear-.
ings for mounting the turbine rotors.
Fig. 11 is a'view similar to Fig. 10, but show
ing radial turbine discs and the bearings for
supporting them.
Fig. 12 is a detail view in axial section, show- ,
ing- a ?exible connection between one of the
turbine rotor discs and its bearings. ,
Figs. 13 and 14 are sectional views through
inner rotor cylinder, designated by the reference
numeral 1 with certain su?lx letters as appro
prlate, whilst the outer'sleeves are designated 8
also with ‘certain su?ix‘ letters as appropriate.
The ?exible axially extending members con
necting the inner foundation ‘rings Ia. and Hit
of the ducted fan blading stages with the respecé
tive turbine rotors are indicated in general by
the reference numerals 9 and ID with suffix let
as appropriate.
the air blading and the turbine blading, respec 50 The several figures of the drawings will now
be described in such detail as seems necessary.
Referring to Fig. 1, it will bev noticed‘ that
In all the illustrated arrangements it will be
assumed that the gas and air flows are from right
to left, the four rows of turbine bladingbeing
numbered respectively i, 2, 3 and 4, whilst the two
‘ air screws or rows of ducted fan blading are des
ignated I and II.
In Figs. 1 to 9' the foundation rings of the ducted fan'blading are‘ indicated at Ia and Ho. ' 1
It will be appreciated from an inspection‘ of 60
Figs. 1 to 9 and a perusal of the description of
these ?gures that in all the arrangements illus-.
trated in these ?gures the four contra-rotational
- intercalated stages of thepower turbine blading
I, 2, 3 and 4 (Fig. 14) are- carried on two rotors
variously constructed as hereinafter described in
detail, namely what are herein for convenience
the blading stages i and 2 of the power turbine
have inner foundation rings la and 2a whilst the
blading stages 3 and 4 of this turbine have outer
foundation rings 3?) and 4b. It is to be assumed
that the blades are in most arrangements secured
in the foundation rings by the provision of roots
on the blades engaging in axial grooves in the
foundation rings, as indicated by the dotted lines
‘such as If and 41‘. On the other hand, the
shrouding such as id and 4c'in Fig. 1 'can' be
assumed to be integral with the evenly circum
ferentially distributed blading in' the stages I and _
4, each 'blade carrying a segment ‘of shrouding.
In Fig. 1 the inner foundation ring ‘la of the‘
turbine blading stage I has an inward ?ange lg
which is riveted to the outer periphery of the
dished disc 5. which is provided with a cylindri
inner one, but these terms arein no way related
to mean blade diameters: wthese rotors are car 70 cal ?ange 5b between which and the inner cylin
drical surface of the foundation member 2a of
ried from a shaft or axle preferably but not
stage 2 is the labyrinthine packing gland 5c. The
necessarily in the manner illustrated in Figs. 10,
foundation .ring 2a has the internal radial ?ange '
11 and 12 of the accompanying drawings and
2g which is riveted not only to the outer pe
as described hereinafter with reference thereto,
through annularly dished discs such as 5 and 75 riphery of the dished disc 6 but also to the inner
- called an outer rotor cylinder structure and an
2,41 1,124
radial ?ange 1a of the connecting sleeve ‘I which
at its‘other end has a‘ ?ange ‘lb riveted to the
inwardly projecting vsegmental lugs 49 formed
on the‘ shrouding ringlc of blading-stage 4 of
the power turbine; thus is constituted the inner
rotor cylinder, carrying stages 2 and 4. It is to
‘ be understood that the rivets may be replaced
are formed directly on the outer ends of some or
all of the turbine blades. The boundaries of the
‘gas and air passages are formed by the bridge
pieces Ho, '41) which are integral with the blades,
and which butt together to form a coinplete cir
cle. There may, however, be fewerair blades
than turbine blades in the row.
There may be an annular recess 4a: as shown.
The outer rotor cylinder of the power turbine
arrangement shown in Fig. 4 only differs
is similarly constituted namely by the provision lit in The
from that shown in the preceding ?g
of the axiallyextending connecting sleeve 8 hav
ures in that the member 9 is integral through a
ing a ?ange 8a riveted or bolted to the segmen
semi-swan-neck part 9a’ at the centre of the
tal external ?ange on the segmental shrouding
foundation ring Ia. the right-hand end of the
ring Id and having a ?ange 8b riveted to the
part 9 being connected to the shroud ring Id
outer foundation ring 3b.
15 as shown in Fig. 3. There is also the difference
The foundation ring Ia in Fig. 1 is shown as
regarding Fig. 4 that there is a common founda
having the integral axially extending cylindrical
tion ring IIa and 4b between the fan blading II
member 9 with the “swan-neck” portion 9a, the
and the turbine blading stage 4, plus the cylindri
right-hand end of which member 9 is connected
by radial rivets at 91) to the right-hand end of 20 cal ?ange 4y extending outwardly around the
a cylindrical extension to of the radial ?ange ' foundation ring 32), with labyrinth packing 42
therebetween as shown.
by screws or nuts and bolts.
.- The foundation ring 11a of the second row II
In the arrangements illustrated by Figs. 1, 2, 3
and 4, the ?rst row I of turbine blading is me
of the ducted fan blading has integral with it the
axially extending‘cylinder it which at its left
chanically connected with the third row 3 there
outer foundation ring lib of the turbine blading
outer foundation or shrouding rings respectively,
25 of through‘ the outer rotor cylinder comprising
' hand end joins integrally as shown at we the
connected by the essential member 8. In the
arrangements shown in Figs. 5, 5, 7, 8 and 9, on
- It will be noticed that the turbine outer founda
other hand, it is the second and fourth rows
tion ring tlb has a cylindrical ?ange 3h extend
ing into the swanmeck Eda and provided with 30 of the turbine blading which are connected to
the outer rotor cylinder. In all cases the ?rst
ridges as shown to constitute labyrinthine pack
I of ducted fan blading is mechanically con
ing against escape of gases from the radial gap
nected With the ?rst and third rows of power
between the turbine foundation rings 3?) and db.
turbine blading at the outer periphery of the lat
At ml) is shown one of a plurality of radial ven
although the invention is not limited in this
tilation holes in the axially extending member
iii to allow turbine, gases which may pass the
1 Referring to Fig. 5, the ?exible axially extend- ,
labyrinth ?ange db, to escape into the air duct
ing swan-neck member 9, 9a is connected by the
(not shown).
The arrangement shown in Fig. 2 differs only 40 welds at 90 and 9] as shown between the short
cylindrical extensions on the left-hand ends of .
from that shown in Fig. 1 in the main in that
the foundation ring Ia and the shrouding Id.
the turbine blading stage 2 is provided with the
The connection of the ducted fan foundation
outer shrouding 2d, whilst the member 8 of Fig. 1
ring 11a is by the cylindrical extension Ill welded
is not bolted or riveted at its ends to the shroud
at its left-hand end at l?d to the cylindrical outer
ing Id and foundation ring 3b but is articulated
portion of the externally ?anged shrouding lid
with respect to these members as indicated at 811
(as shown) the radial ?ange being in this case
in the manner hereinbefore set forth. Further
riveted to the left-hand radial ?ange of the sleeve
more the member 8c is omitted and the member
9a, 9 is provided with the internal ?ange 90 with . B which at its right-hand end is welded at 80”
to a left extension of the shrouding 2d.
the cylindrical extension 902 riveted to the ?anged
The further modi?cation illustrated by Fig. 6 ,
' shrouding ring id.
is characterised by several minor features,‘ as
The arrangement shown in Fig. 3 differs from
follows: The cylindrical member 8 has its ?anges
the arrangement shown in Fig. 1 in the follow
by “axialf’ rivets, at its right-hand
ing respects: all the turbine blading stages have
end to the ?ange formed on the turbine blade
inner foundation rings id to Ila. The stages i
shrouding 2d, and at its left-hand end to a simi:
and 3 have outer shrouding rings‘ id and 3d,.
lar ?ange on the fourth turbine stage shrouding
which are preferably formed in segments each
dd radially riveted at Hie to the doubly ?anged .
segment being integral with one blade. The use
end Iii)‘ of the'?exible cylinder ill, near the right
of complete rings is not, however, excluded, and
hand end of which is the radial ?ange lllg secured
these of course will be relatively light in weight
stage it.
compared with foundation rings. The member I 60 by the hollow rivets lllh to the inward ?ange of
the ducted fan foundation ring Ila, as shown.
The ?ange I09 is extended outwards at I02‘ to
eted ?anged joints, whilst labyrinthine packing
terminate in a cylinder portion I 07' bridging the
5d may be provided, as shown.
gap between the ducted fan foundation rings Ia
A member 8, likewise, connects the shrouding
and 11a.
ring id with the shrouding ring 3d. The axial- .
by Fig. 6, fur
1y extending member 9 is of more elementary
thermore, the turbine shrouding id has an out
form than is shown in Figs. 1 and 2, being a sim
ward ?ange Id’ secured by hollow rivets I d" to
ple integral extension of the ducted fan founda
an internal ?ange 9g on the ?exible member 9 '
connects the foundation rings 2a and 13a by riv- _
tion ring Ia, and riveted or bolted at its right 70 which at its other end has an outward ?ange 9h
hand end to a short axial extension 80’ of the
secured by hollow rivets 97' to an inward ?ange
member t.
the foundation ring Ia. Furthermore, the
Furthermore, the ducted fan blading stage II
?ange 99 has a cylindrical extension 9k overlap
is shown integral with the turbine blading stage
ping the shroud 2d, with labyrinthine packing 9h’
4 as a “double-tier” stage in which the fan blades 75
therebetween. The hollow rivets 9i and I (In have
' 7
agraph is‘per se broadly claimed in oopending
application Serial No. 518,174, ?led January 13,
?owing through them cooling air inducted by the
air blades, while the hollowjrivets Id" prevent
1944, and is only claimed herein strictly subordi
the establishment of a hot pocket by gases pass
‘ ing the labyrinth packing between the station
. nately to the main features of the present inven-
ary structure and the facing surfaces of member
Id and 9.
‘Fig. 9 of the drawings of the present applica
tion shows an arrangement which differs only in
details‘ (which should be readily apparent now)
The arrangement of Fig. 6 enables the foun
dation rings Ia and Ila to be of a different ma—
terial from the ?exible members in and 9. Also, ' from'the arrangement shown inFlg. 8. At 23 is
owing to the cooling effect of the air stream pass 10 shown in dotted lines the ?nal blading stage of
the compressor turbine, namely the'turbi'nedrlv-'
ing through the hollow rivets, thematerial- of
ing the. compressor which supplies the combus
the said foundation rings Ia and 11a may be
chosen'without regard to its suitability for high ‘ tion» chambervsupplying the gas for said com
pressor turbine. .In' Fig. 9 are fragmentally.
temperature operation. It may, for example, be
an aluminium alloy.
Referring to Fig. 7, the per. se constructions
of the ducted fan and power turbine need no
‘particular description after perusal of the de
scription of ‘and the inspection of Figs. 1 to 6;
except‘ by the hereinbefore set forth means of
connection of the two contra-rotational tu'rbine
rotors to the respective foundation rings Ia. and
11a ofthe ducted fans. Namely, the comparative
15 shown labyrinth packing members 21 and 28
separating moving parts from the last stage 26
of the compressor turbine. There is also shown
in Fig. 9 at 2dr 2. double tongue projection formed
at the outer end of the blades of stage 2, engaged
20v and held by rivets in a correspondingly formed
extension 8:: of the connecting member 8, thus
forming the foundation ring for the blading'stage
2. There are also shown in this Fig. 9 the ven
tilation holes VI and V2,'and the cylinder V3
ly shorter axially extending members 9 and it
are connected to relatively short overlapping axial 25 for preventing the light alloy foundation rings
of the ducted fans being subjected to too high
extensions of the air ‘blade foundation rings Ia
and Hay respectively, by the tapered pins I2, as . temperatures.
Fig. 10 shows how the dished discs 5 and 6
and for the purpose hereinbefore set forth. It
can be ‘contra-rotationally carried on ball bear
will also be'noted from an inspection of Fig. 7 4
that the discs 5'and B may be dished oppositely 30 ings about a shaft which, as an’ example, is a
stub shaft extension 29 of the compressor tur
in contrast with'those indicated in Figs. 1 to 4.
' In the arrangement illustrated by Fig. 8 the
power turbine is shown by way of example’as.
in Fig. '7, but the connection of the ducted fan
blading to the turbine rotors is different in a 35
bine, being integral with or secured to the disc
26a of ‘the last stage 26 (Fig.9) of the compressor
turbine. In the ‘illustrated example the annu
larly dished disc 6 is secured at its inner periph
ery by rivets 61) (or bolts) to a radial ?ange 30
respect as follows: In this figure the foundation‘
ringsIa and Ho are of “light alloy” and are con
on the left-hand end of the sleeve shaft 3| car
rying at that end the outer race of a ball bear
ing 32 the inner race of which is- carried on the
nected by the steel, axially extending membersil
and ID, preferably of “swan-neck” form generally
similar, as‘an example, to that shown in Fig. 1 40 stub shaft or extension 29. The bearing 33 at
the right-hand end of the sleeve shaft 3| ‘is car
ried within a member 34, the outer cylindrical
. as regards the members 9b and 8c, and similarly
as regards ducted fan stage II illustrated by Fig.
'5 at I0, but with the following changes, namely:
The member .8,c (compare Fig. 1) at its right
hand' end is riveted or otherwise connected to 45
theright-hand end of the outer ?exible cylinder.
part of which is connected by taper pins 35 from
a cylindrical hub part 36 of the disc 26a for ac
commodating radial differential thermal ‘expan
The inner periphery of the annularly dished
' 9 which at its left-hand end is formed as fol
. lows for its connection to the foundation ring Ia.
disc 5 is rigidly attached to an outer sleeve shaft _
31 relatively rotatable with respect to the sleeve
The left-hand end of the ?exible cylinder 9 is
. formed with 'a radial flange portion 91 integral 50 shaft 3| through the ball bearings 38.
Cooling of the ball bearings and their sleeve
- with a re-entrant cylindrical ?ange 9m, thereby
shafts may be effected, together with some cool;
providing as shown the annular channel holding,
ing of the discs 5 and 3 or 5a and 6a and the blade
by the. rivets 9n, the inserted extension edge of
foundation‘ rings, by the introduction of cool
the foundation ‘ring Ia, as shown. The other"
foundation ring 11a is similarly drivingly con 55 ing air at the outer end of the stub extension 29
of the compressor turbine shaft, which extension
nected to the other rotor' of the power turbine,
is made hollow for the purpose and furnished
as can be readily seen by examination‘ of Fig. 8
with radial holes 2911 providing outlets into laby
of the accompanying drawings. In Fig. 8 there
rinthine passages‘ about the sleeves and bearings,
is also shown the following adjuncts,- viz:
An annular shield disc 20 is clamped by its cy 60 with ?nal-discharge intospaces from which the
air may emerge to join the gas stream.
lindrical portion by the rivets 9b, at the inlet
end of the ducted ‘fan stage I, and an annular
, de?ector disc 2| at the left-hand end of the
. . Fig. 11 is similar to Fig. 10, only differing-there
_' from, as hereinbefore indicated, in that instead
foundation ring IIa: there are also holes 11, \as
_ of the dished discs, there are the radial
flexible cylindrical members 9 and I0.
' some further ?exibility to the discs 5a and 6a -
shown, in the radial parts holding the'foundation 65 and So each‘ having inner cylindrical parts 5.1:
and 61: connected by taper pins 39 and 49 to the
rings Ia and 11a, which rings necessarily have
sleeve shafts 31 and 3| respectively. For giving
cylindrical clearance from the outer parts of the
Thus, as
shown by the'short arrows 22 and 23, cool air,
due to pressure difference, flows back to the axial 70.
they may be provided with the annular ‘grooves
indicated, at ll.
Finally, Fig. 12 illustrates the ?exible connec
grooves 24 in' the foundation ring 11a to and
through the holes p and then through the grooves
tlon' of a disc, for example 5a, to the sleeve shaft, ~
25 in the ring Ia, as shown by the arrow 25, to
for example 31, by the cylinder 42. .
It will be understood that there may be more
‘the shield 20 to be returned to the annular stream
of ‘inducted air. The subject matter of this par
than four‘l‘ow pressure turbine stages. For in
from to said ring, and comprising everlapping
portions, and radial tapered pin's uniting said por
stance, ii there are six turbine stages the disc
or dished web for the .?rst rotating member may
carry or be connected directly to the blading or
3. In an internal combustion turbine structure,
the ?rst turbine stages while the rows or blad
ing of the third and ?fth stages are carried by 5 the combination of a power turbine having axial
?ow turbine blading and air blading carried and
exteriorly located‘ foundation rings. The disc
driven by a turbine rotor outwardly of said tur
or dished disc for the second rotating member
bine blading, at least one air blading stage hav
may carry or be connecteddirectly to the blad
ing a'ioundation ring at the base of the blading
ing of the fourth stage whilst the rows of blad
ing of the second and sixth stages are carried by 10 row so as to form a self-supporting structure
which is carried by said rotor of the power turf
foundation rings located’respectively interiorly
bine, and an axially extending member capable
and exteriorly of the bladlng. The exterior cy
of radial ?exibility for accommodating diil'er
lindrical and/or "swan-neck” connections for
ential thermal expansion, said member being con
driving the ducted fan stages may be made re
spectively with the ?rst and sixth low pressure
nected to said rotor and extending axially there- ‘
from to said ring and terminating in radially
spaced cylindrical portions, and the inner founda
tion ring of said row‘ of ‘air blading having a
of the inner and outer rotors ‘or the power tur
cylindrical portion extending‘ between and se
bine'as hereinbefore described may involve the
progressive building up of. the separate constit 20 cured to said portions.
4. In an internal combustion turbine structure, '
uent parts and intercalated blading stages of
the combination of a power turbine having axial
these rotors, in the axial direction, and this sub
flow turbine blading and air blading carried and
_ject matter,'which can be carried'out in other
driven by a turbine rotor outwardly of said tur- .
ways, per se forms the subject matter of copend
ing application Serial No. 518,167, filed January 25 bine blading, at least one air blading stage hav
ing a foundation ring-at the base of the blading
13, 1944i.
turbine stage structures.
It is now herein pointed out that the structures
I claim:
1. In an internal combustion turbine structure,
an air impeller comprising a power turbine com
row so as to form a self-supporting structure
which is carried by said rotor of the power tur
bine, and an axially extending member capable
prising a. plurality of intercalated stages of axial 30 of radial ?exibility for accommodating differen
tial thermal expansion, said member'bein'g con
flow turbine blading constituted as inner and
nected to said rotor and extending axially there
outer rotor members, at least one of said rotor
from to said ring and having a cylindrical ex
members comprising axially spaced ring supports
tension arranged to constitute a heat shield be
for a pair of stages of turbirieblading and a co-.
axial sleeve member interposed between and con 35 tween the driven structure and the hotter turbine
necting said supports, and air blading carried
5. In an internal combustion turbine structure,
‘and driven by said rotor members, at least one
an air impeller comprising a power turbine hav
air blading stage having a foundation ringat‘
ing axial ?ow turbine blading and air blading'
the base of therblading row so as to form a self
carried and driven by _a turbine rotor outwardly
supporting structure which is carried by one of 40 of said turbine blading, at least one air blading
said rotor members of the power turbine, and an .
stage having a foundation ring at the base of the
axially extending member capable of radial ?ex
blading row so as to form va. self-supporting struc
ibility for accommodating di?erential thermal ex
ture which is carried by said rotor of the power
pansion, said axially extending member being , turbine, and an axially extending member capa
connected to one of said rotor members and ex
ble of radial ?exibility for accommodating diii'er
tending axially therefrom to said foundation ring.
ential thermal expansion, said member being
2. In an internal combustion turbine structure,
an air impeller comprising a power turbine having
axial ?ow turbine blading and air blading car
' connected to said rotor" and extending axially
said turbine blading, at least one air blading stage
having a foundation ring at the base of the blad
; ling row so .as to-torm a self-supportingwstrucv
spaced therefrom to provide an annular channel
therefrom to said ring, and comprising a cylin
drical portion within the inner substantially cy-.
ried and driven by a turbine rotor outwardly of 50- lindrlcal surface or said foundation ring and
for cooling air whereby said ring and associated
structures are protected from the heating e?ect of
. ture which is carried by said rotor of the power
adjacent turbine parts and of turbine gases, and
turbine, and an axially extending member capable ‘55 means providing an induced air circulation in
‘of radial ?einbility for accommodating di?eren- . said channel.
_ tial thermal expansion, said member being con“
nected to said rotor and extending axially there-_>
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