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Патент USA US2406473

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Aug. 27, 1946.
2,406,473
E. P. PALMATIER
FAN DE-ICING OR ANTI-ICING MEANS
Filed Sept. 3, 1943
2 Sheets-Sheet l
INVENTOR.
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ATTORMfK
Aug. 27, 1946.
E. P. PALMATIER
2,406,413
FAN- DE-I‘CING .OR ANTI-ICING MEANS
Filed Sept. 3, 1945
2 Sheets-Sheet 2
2,406,473}
Patented Aug. 27,, 1946
‘if . UNITED STATES * PATENT.
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2,406,473
,
. FAN fin-10min on ANTI-ICING MEANS
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' Everett 1’. Palrnatier, Upper lVIontclair,
.‘,i1as--* 7
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signor‘to Curtiss-Wright?orporation, a-corpo
ration of Delaware
,Applicat'ion'september 3, 19,43,‘ Serial ire-{501,157
. 1 calm. (o1..244-'~1s4)
connecting memberl‘i-is'
‘My invention! relates»? to L- de-iciingi _ or anti-icing
arrangements for applying a ‘liquid’ medium to
an annular series of blades ‘on an aircraft.
tilize'd_ for
thispurpos'e,
_
the respective angular sides thereof engaging'the
spinner'ii and disk iii and the surfaces WhiChithuS
engage being riveted, welded or-otherwisesecured
‘ "In-accordance with my invention,v a suitable liq
‘together'in any suitablemanner.
luid medium'is applied tolthe aforesaid blades, this
"liquid-medium serving either tomelt such ice as _
j'majgr-“ha've'been formed on thefbladesor to pre
:vent theformation of icethereon.
Further in accordance with my invention, the
“aforesaid liquid mediumpasses througha'eonduit
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Projecting" from and carried by the‘diski flange ‘
H are therotatable fan blades-B whichiform'lthe
fan rotor, the blades VB being-angularly related in
suitable manner to-the path of movement thereof
through‘the ‘air so that, when rotated, theyjdirect
of air rearwardly toward the vengine: ‘I’.
system under the influence of ‘centrifugal‘action , E Lafs'tre'am
‘or independently thereof and vengages the‘ exterior . lljisposedrearw'ardly of the rotor blades 13 is‘the
“set of?xed ‘fan‘blades Blvwhich 'forrnealcir‘cular
"stator, the’ blades lB! ‘being'angularly ‘relat
surfaces .of‘jthe blades ‘for. ‘the useful purpose
” ' Various other ‘objects, advantages and features 15 suitable ‘manner to the rotor blades-B1 ‘In‘jthe‘
;of='-'my‘_~invention will become apparent trom'ithe 1'3 example vshovvn, ‘the
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"to theicowling v2v andtoga housingilsfastened
-’following detailed description. > '
stated-‘above.
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‘suitable-manner to ‘the engine}! v or ‘the, n,
‘ 'Myinventionr'esides in the-fan-de-iCing or'anti
icing means, arrangements and combinations of
thereof.
20
:the‘characters
hereinafter described andclaimed.
‘ “For an understanding of my‘invention and for
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‘ When‘ the aircraft engine lis in operation, the
shaft 3, the hub 5,, the propeller blades‘ Bfand‘ the
spinner '8, rotate, asa _unit._ ‘The diskv In '
an illustration of one of the forms thereoL'ref'; '
’
‘flange 1! rotate with'the'spinner.Band, t
‘the rotor blades 13 (direct-a stream‘ 9?
'eré'nce-is tojb‘e-hadto‘ the accompanying drawings,
?
f
toward the engine ‘I ._ _ nearest-cashew 1
2.5 yiardly
‘of. air-,rea'ches‘said engine ‘I is suitablyfdeflected‘
broken
- r Fig. 2away,
is a showing
vertical one
sectional
form ofview,
my invention‘;
*partly "in ‘ .by thestatoribladesBL
'1, " ,_
,
Inv accordanc'ewith the in ention, ‘rhea: an'gee
elevation, taken on the line '2~—2 of Fig. 11 looking ,
‘ment described above has‘, associated ‘theliéwith
in’the direction of the arrows;
Fig. 3 is a transverse, verticalsectional-view,“ 30 suitable ‘means ‘for supplying.deeicing'liduid to
in’whichz'
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'~" Figure 1‘ is a front elevational ‘view, partly
one or both of the fans describedabove. \, l‘lldthi's ' _
partly in elevation, taken onthel line ‘3-3' of ‘Fig,
end, as shown-in Figs. ‘144;;inclusive,_a magma,
2 looking in the :direction of the arrows;
Fig. 4 is an enlarged elevational view, partly'in "
‘.knownil as a “slinger” ring-is riveted, Welded ,or
otherwise, suitably securedto the ,rear, faceof the
5.Fig..'5‘ isan enlarged elevational view, partly in 35 disl<_l€i,.the ring Mlbelngshapedto formja circuT
section, showing a featurelof the invention; and '
section, showing a modi?cationlofJtheinvention. ‘ lar chamber open. throughout‘itslength, at thew ‘
‘inner sidestheréofr .‘AI conduit 15 which risen.
Referring to Fig. l, l designates the aircraft
ehored'in position in any-suitable niannengfar I
engine with which, vin suitable man'nenthe usual
example, by attachment to the engine nose :4, ,is.
circular cowling 2 is ‘associated.’ The ‘engine?!
operates the propellershaft 3 which extends for‘ 40 supplied withthe de-icing liquid, theylatteribeing
discharged from said conduit [5 into the ringlA
wardlybeyond the engine nosed and‘ there car
ries the propeller hub '5 having the propeller
at any suitablerate.
: >
* r .
-A' plurality ofpipes .IB supported in suitable
iblades 6' projecting therefrom. 'Assooiated‘with
the hub 5 is a housing ‘I for the motor and asso
ciated ‘apparatusope'rative, as known‘ in the art,
for ‘changing the pitch of'the propeller blades 6.
A‘spinner 8 encloses the'hub ~5-and housing '1, the
blades’ 6 extending through the respective open
45
manner,“ for-example,;by seating the respective
opposite ends vthereofin passages formedin-the
ring M and-in thedisk flange Hare utilized for
passing {Ge-icing liquid from'the ring Hi .andi'dis
charging it ‘at the>leading edges ‘of the respective
ings ‘provided therefor'in the 's'pinner’dwhich, in
rotor blades-1B‘ at“ or adjac'entlthe ‘roots thereof.
indicated at 9 whereby said hub Sand the spinner‘ '
is provided forea'chrotor-bladeB.' ’ \
a conventional manner, is securedto the hub-5 as 50 In the example-shown andprefer'ablm-one pipe‘ I6
Bare rotatable together as a unit.
,
The spinner 8 extends just, to the rearv of the
blades 6 and'the otherwiseopen, circular-end
thereof isjclosed by a dish Hlwhich‘ comprises a
rearwardly extending circular ?ange H, saidtdisk
I 0 beingprovided with a central, opening through
which'the aforesaid shaft 3 extends
close-?n,
ting ‘relation. The disk 10 is secured to‘ the spin
ner_8 in any suitable mannerso as to be rotatable‘.
therewith ‘as a unit. As‘ herein shown, a circular
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A plurality?ofpipes I‘! s y'lpp'ortedffor example‘,
in :the same manner as described ‘,WithrespQect‘ to
.
as'
the‘pipes ’| 6 are utilized'for passing de-icingiliqf
' the ring m and discharging it so‘ that it
uid from}
engages the leading edges of the stator" blades Bl
at or adjacent’the roots thereof. In‘the form of
the inventionshowmfour ofthe pipesfi'l ~aliepro
vided aniithese are symmetrically relatedgtnt: acl’l
~ other‘ around the - periphery‘ ‘of ‘the stator."
"How? i
,1 2,406,473
3
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I ever, it will be understood that more or less of
the pipes; I 'Imaybe provided as desired.
7
During operation of the aircraft engine as ‘de
scribed, the ring I4 togetherwith the pipes I6
across the fan blades B from theleading edges to
the trailing edges thereof and some of this de
icing liquid may pass onto the statorblades BI. '
, Further, some of the de-icing liquid is entrained
and I1 rotate as a unit with the disk In and ‘its!’v ~ in the airstream produced by the rotor and car
ried thereby. into engagement with'the surfaces
V
When it becomes desirable to operate'the ‘de'; I‘ 'Z' ' of the stator blades B I .
icing system, a suitable de-icin'g liquid such, ‘for
. .In view of the foregoing description, it will be?
example, as alcohol, glycerine or the likeis sup: 4‘ vfcome apparent that, as regardseither or both the
7 plied to the pipe I5 under suitable pressure. 10 rotor or stator of a, fan cooling arrangement for
From the pipe I 5,,the de-icing liquid passes into
an aircraft engine, a I ' provide arrangements for
the ring I4 and, by centrifugal action, is distrib
supplying'liquid to"the‘ blades in proper propor
uted throughout-the circumferential length there- a ' tions to e?ect the desired de-icing action.
of. Accordingly, the ring I4 serves as a chamber
With the forms of my invention herein dis
.. providinga source of supply of, the de-icing liquid 15 closed, theUde-icingliquid is applied; effectively
for the pipes I6 and I‘! through which the de
to bothsides of each fan blade-Whether rotor or .
icing liquid'passes to the roots of the rotor and
stator, throughout substantially the ‘entire area
stator blades B and BI, said de-icing liquid pass
thereofn Particularlyhas regards the formof my
ing through the pipes I5 and‘ I6 and being dis
invention illustrated in Fig.5, the liquid ole-icing
tributedalong the surfaces of the respective rotor 20. material isapplied effectively to each rotor blade}
blades Bfrom the leading edges thereof by cen
at the tip end area thereof. The arrangement
trifugal action as will be understood.
last noted is particularly advantageous because
hereinbefore stated, it is desirable that one
it has been ascertained thatthe leading edge area
of the pipes. I6 be provided for each rotor blade
together with the areaat the tip end of each rotor .
VB. 'However, as regards the stator blades BI and, 25 fan blade are critical ,fromthe icingviewpoint.
fas stated,;a substantially smaller number ofthe
In, the appended claim, the expression ‘fde- I
pipes "are provided than there are blades BI.
icing’,’
shall be understood asrdescribing true de
; .As will be understood from the foregoingdescrip
icing wherein that ice is melted which, previously,
tion, the pipes .I ‘I sweep past, the roots of the'stator . had‘been‘
formed onthe' fan‘blades-and said ex
blades BI and, since each of the pipes I1 is trav 30 pression shall
‘also beconsidered as. describing
ersed by vthe de-icingv liquid,;it results that each
an operation wherein the fan blades are subjected H
stator'blade BI receives its share of the totalsup
ply of deg-icing liquid which is distributed by the
pipes I'I.; ,The air stream produced by the rotor
to the action of an agent which“ positively pre
vents the formation of ice thereon.
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‘ a '
.,While the inventionhas been described with
respect to certain particular preferred examples
blades 3 aids in. the distribution of the 'de-icing
liquid along the surfaces of the stator blades BI.
Furthensai-d‘stator blades BI may receive some
I which give satisfactory results, it will be under? 7
stood by'those skilled in'the art after understand
de-ic’ingj liquid directly from the rotor blades B.
With .the'form of 'myi‘nvention hereinbefore ; q ing the invention, that various changes and modi- -
?cations may be made without departing from the
' described, the ring I4 togetherrwith the pipes I6
and I1 rotate as a unit in order to effect the de
icing operation. , Each pipe ,I6 is immovable with
spirit and scope of the» invention and it‘ is in; .
tended therefore in the appended claim to, cover
_ allsuch changes and modi?cations.
irespect'to the rotor blade B with which it is asso
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What is claimed as new and desired to bese;
ciatedg, However, the. pipes I1 rotate with respect _, =
‘to. the stator blades _BI and the de-icing liquid is 45'.curedby
In an Letters'Patent
aircraft, iii-combination,
is:
,
a'- streamlined
"
distributed therefromonto the latter. a -
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spinner, an annular'cowling concentrically ,sur
_ With; the form of -my ‘invention referredto
" rounding said spinneriand de?ning therewith an
above,<pip,es‘ I Ii have been described for conveying
- the de-icingliquid fromqthe
ring
V
annular air entrance channel, a rotary'fan com
I4 tothe. blades
': prising a hub whose surface is contiguous with
the invention is ' 50 the’spinner surface, having a large pluralityof
not 'to belimited to said pipes I6. , Obviously,
7
the
B. Itshall be understood that
diameter of thering I4'_may besuch that it is
fan blades extending-therefrom and sweeping said
to the cowling 2 or equivalent structure for ?xing
said pipe IBwith respect'to' the'rotor blades B.
ing from said collector outwardly to points adja
annular channel, a stator fan comprising a large
located closely adjacent the'roots“ of the blades B
plurality of stationary fan blades disposed in a
and, ,if so, the liquid preferably passes
a
to the re
.lspective bla des B through‘ orifices or nozzles 55 plane parallel to the rotary blades and extending
formed in said ring I 4;
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across'said annular entrance in series relation
withthe rotating blades, an annular collector
Referring to Fig. 5, I have ‘shown a modi?ca
within 'said'rotary fan hub rotatable therewith;
tion of the invention wherein a'pipe I8 is ?xed
means to feed a de-icing ?uid thereto, ducts lead
60
The pipe I8 terminates in an angular section I8a
provided preferably‘with ‘a plurality of nozzles I8b
which-face towardthe'leadlng edges of the re
spective rotor blades B as they arrive 'in'succes-k
sion opposite the pipe section I 8a.’ As will be
: edges ‘of said rotaryfan blades, and ducts fewer in
number than the number. of blades leading. from
understood, ' 'de-iclng¥liquid~may*be» stored in a
tank I9 and, under-the control of a_pump 20,.
said collector to points on said hub close to the
leadingv edges of said stator fan blades~ for spray
ing, understhe in?uence of centrifugal force, a
the de-icing liquid may-be‘ supplied through the
d V
\ under suitable pressure and ejected con-l
- uniform spray of- ?ui-d in advance of all the lead;
tinuously from the nozzles I8b. As the rotor 1'0?
tates,‘ each of thebladesB thereof receives a por-.
ing edges of said statorblades as the .rotaryfan
hub rotates relative?thereto, whereby. the sheet .
tion of the total supply of, the de-icing .liquid '
of spray thus formed impinges, atleast in,part,.
upon the all of the stator fan blades for removal
which is thus ejected from the nozzles-I8b.._ For;
ward movement ofthe fan blades“ B through the,
air causes distribution of‘ the .deigicing. liquid
cent the roots of the leading, edges of the several ,
rotary fan blades for conducting fluid from- said
collector ‘for spraying, under the in?uence ofcen
trifugal force, a spray of ?uidalong the-leading
. of ice therefrom.
75
,7 EVERETT r. PALMATIEaQQ: '
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