US2499831A - Fan deicing or antiicing means - Google Patents

Fan deicing or antiicing means Download PDF

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Publication number
US2499831A
US2499831A US507759A US50775943A US2499831A US 2499831 A US2499831 A US 2499831A US 507759 A US507759 A US 507759A US 50775943 A US50775943 A US 50775943A US 2499831 A US2499831 A US 2499831A
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fan
blades
hollow
hub
means
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US507759A
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Everett P Palmatier
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Curtiss-Wright Corp
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Curtiss-Wright Corp
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid

Description

March 7, 1950 P, PAL MATIER 2,499,831

FAN DEICING 0R ANTIICING MEANS Filed (Kit. 26, 1943 Patented Mar. 7, 1,950

FAN DEICING OR ANTIICING MEANS Everett P. Palmatier, Upper Montclair, N. J., assignor to Curtiss-Wright Corporation, a corporation of Delaware Application October 26, 1943, Serial No. 507,759

7 Claims formed on the fan blades or to prevent the formation of ice thereon.

More particularly, in accordance with my 1nvention, the aforesaid hot gases are caused to.

pass through each fan blade for the purpose stated.

Further in accordance with my invention, a plurality of fan blades are secured to an aircraft spinner or other rotating mount for rotatable movement therewith, each of the fan blades comprising a passage extending longitudinally there through.

Various other objects, advantages and features of my invention will become apparent from the following detailed description.

My invention resides in the fan de-icing or anti-icing means, the fan blade constructions and arrangement of the character hereinafter described and claimed.

For an understanding of my invention and for an illustration of one of the many forms thereof, reference is to be had to the accompanying drawings, in which:

Figure 1 is a vertical sectional view, partly in elevation, showing an aircraft power unit having my novel fan de-icing or anti-icing system associated therewith; I

i Fig. 2, generally, is a front elevational view of the arrangement shown in Fig; 1, a part of this view being taken on the line 2--2'of Fig. 1 looking the engine nose 4 and there carries the propellerhub 5 which comprises angularly related sockets 5a carrying the respective propeller blades 6. Associated with the hub 5, forwardly thereof, is a housing I for the motor and; associated apparatus which, asknown in the-art,- is utilizable for changing the pitchof-thcpropeller blades 6. A spinner 8 encloses the hub 5 and housing 1, the respective propeller blades 6 extending through openings provided therefor in the spinner 8 which,

in a conventional manner, is secured to the propeller hub 5 as indicated at 9 whereby said hub 5 and spinner 8 are rotatable together as a unit. In the form of the invention herein shown, the rear end of the spinner 8 carries the rotatable fan blades B which form the fanrotor, the blades B being angularly related in suitable manner to the circular path of movement thereof through the air. Disposed rearwardly of the rotor blades B are the fixed fan blades Bl which form acir-- cular stator, the blades BI being angularly related in suitable manner to the rotorblades B.

When the aircraft engine I is in operation, the

shaft 3, the hub 5, propeller blades 6 and the spinner 8 rotate as a unit, the rotor blades B directing a stream of air rearwardly toward the, engine I. Before such stream of air reaches said engine I, it is suitably deflected by the rear stator blades Bl.

While a conventional propeller-engine-cowl fan arrangement is shown in the drawings, the invention is not to be considered as limited to this environment. Rather, the invention is directed primarily to the problem of de-icing or anti-icing of cowled fans or blowers for aircraft.

With respect to one or both of the above described sets of fan blades B, BI and, in accordance with the invention, a suitable arrangement is provided either for de-icing the fan blades in the event that ice should form thereon or for. positively preventing the formation of ice on said fan blades. 1

As an example of the invention, I have illustrated on the drawing an arrangement for passing hot gases through each fan blade forder icing purposes. disclosed arrangement is to serve merely as an illustration of one of the many" arrangements which may thus be utilized. Further, it shall be understood that the invention is not to be limited to the use of the fixed fan blades Bl since, if desired, these may be omitted and, if so, the hot gases may be passed directly to the rotor fan bladesB. V 1 .1

In accordance with, the invention, each fan blade. B is formed from a pair of members l0, H) which, as herein shown although not necessarily, are formed integrally with the rear spinner section to from which the sets of members I ll. I 0' project in blade-forming relation. V.

The rear spinner section further. comprises a pair of interior angular "members 8b, 1.80 which extend throughout the entire circular length- 0f the spinner and are disposed transversely toits' It shall be understood that the;

blade BI is formed from a pair of members 20, 20 I which, as herein shown although not necessarily, are formed integrally, at their inner ends, with a circular member 2| and, at their outer ends, with the cowling section 2a.

The circular member 2| comprises a circular angular section 21a which, in suitable manner, is secured to the engine nose 4. This circular angular section Zla forms a channel Ila which communicates with the channel ll defined by the spinner members 8b, 80.

In accordance with the invention, the blade members 20, 20 of each fan blade Bl are suitably spaced from each other by a channel or slot 20a which, at its inner end, communicates with the circular channel Ha, the outer end of each slot 20a being open or unobstructed.

As clearly appears from Fig. 1, the cowling 2 and its section 2a form a circular chamber which is separated into two parts by a circular wall 22 forming a barrier in said cowling 2 between the rotor fan blades B and the stator fan blades Bl.

During the flight of the aircraft and when it becomes necessary to subject the fan blades B and Bi to a de-icing operation, hot gases or a suitable hot gaseous medium is passed under suitable pressure into the aforesaid circular chamber defined by the cowling 2 and its section 2a, said hot gaseous medium being supplied to this chamber, in the example shown, through a plurality of pipes 23 arranged in suitable spaced relation throughout the circular chamber length, these pipes passing through openings provided, respectively, therefor in a circular wall 23a secured interiorly of the cowling 2. Preferably, although not necessarily, the described hot gaseous medium is heated air obtained as disclosed in my pending application Serial No. 503,143, filed September 20, 1943.

Accordingly, for de-icing purposes, the hot gases are supplied under suitable pressure to said chamber defined by the cowling 2 and its section 2a, the hot gases engaging the wall 22 and being deflected thereby so as to pass inwardly through the slots 20a of the respective fan'blades Bl. Thereafter, the hot gases pass fromthe fixed channel I la to the rotating channel' II and, then, said hot gases pass through the slots We of the respective fan blades B, into the front cowling chamber and then pass to the atmosphere by way of the cowling openings 21).

In view of the foregoing description, it will be understood that, in the event that ice forms on the fan blades hereinbefore described, the aircraft pilot or other aircraft occupant may open a suitable valve or the like, not shown, to thereby cause heateda'lr to pass from the pipes 23 and then through the fan blades B and BI for the purpose described. As a result, the temperature of the fan blades is elevated by the hot gases to thereby effectively melt the ice which adheres thereto.

Should .the aircraft pilot obtain knowledge that. heisapproaching an area wherein icing; conditions mayexist, the above noted valve may happened-before sucharea is reached to thereby 4 heat the fan blades in advance and positively prevent the formation of ice thereon.

In the appended claims, the expression deicing shall be understood as describing true deicing wherein that ice is melted which, previously, had been formed on the fan blades and said expression shall also be considered as describing an operation wherein the fan blades are subjected to the action of the hot gases in order to positively prevent the formation of ice thereon.

While the invention has been described with respect to a certain particular preferred example which gives satisfactory results, it will be understood by those skilled in the art after understanding the invention, that various changes and modifications may be made without departing from the spirit and scope of the invention and it is intended therefore in the appended claims to cover all such changes and modifications.

What is claimed as new and desired to be secured by Letters Patent is:

1. In an aircraft, a set of hollow fan blades forming a fan stator, a set of hollow fan blades forming a fan rotor, means for rotating said fan rotor, and means for passing a fluid through all of the fan blade hollows, said last named means being effective as regards the fan rotor blades while they rotate.

2. In an aircraft, a set of hollow fan blades forming a fan stator, a set of hollow fan blades forming a fan rotor, means for rotating said fan rotor, and means for passing a fluid through the stator and rotor fan blade hollows in succession, said last named means being effective as regards the fan rotor blades while they rotate.

3. In a fan system, a fan hub, hollow blades carried thereby, the hub having passages communicating with the blade hollows, a hollow shroud encircling the fan blades having a passage therein, in the path of said blades during their rotation, in communication with said blade hollows, and hollow stator blades carried by said shroud, the hollows of which communicate with the shroud hollow, said stator blades being disposed in an annulus coaxial with and parallel to the fan blades.

l. In a fan system, a fan hub, hollow blades carried thereby, the hub having passages communicating with the blade hollows, a hollow shroud encircling the fan blades having a passage therein, in the path of said blades during their rotation, in communication with said blade hollows, hollow stator blades carried by said shroud, the hollows of which communicate with the shroud hollow, said stator blades being disposed in an annulus coaxial with and parallel to the fan blades, and means including said hub and shroud to direct a fluid medium through said stator and fan blade hollows.

5. In a fan system, a fan hub, hollow blades carried thereby, the hub having passages communicating with the blade hollows, a hollow shroud encircling the fan blades having a passage therein, in the path of said blades during their rotation, in communication with said blade hollows, hollow stator blades carried by said shroud, the hollows of which communicate with the shroud hollow, said stator blades being disposed in an annulus coaxial with and parallel to the fan blades, and means including said hub and shroudto direct-a fluid medium serially through said stator and fan blade hollows.

6. In a fan system, afan hub having radially extending axial flow blades thereon, said blades together sweeping an annular fan blade zone, a hollow shroud embracing said fan, radially extending axial flow hollow stator blades extending from said shroud and disposed in an annular zone parallel to and coaxial with the annular fan blade zone, said zones lying between said hub and shroud and together forming an axially extending passage for a fluid working medium operated on by said fan blades, and means to direct a second fluid medium into said shroud hollow and radially through said stator blade hollows.

7. In an axial flow fan system, a hollow hub having a substantially cylindrical periphery, a plurality of pitched hollow blades arranged around said hub, a substantially cylindrical shroud embracing said blades and defining with said hub periphery an axially extending annular passage through which a working fluid passes for engagement with the external surfaces of said blades, and means establishing free com munication between said blade hollows, said hub hollow and through said shroud for a second fluid isolated from said working fluid, said blades being fixedly secured to said shroud.

EVERETT P. PALMATIER.

REFERENCES ITED The following references are of record in the file of this patent:

UNITED STATES PATENTS

US507759A 1943-10-26 1943-10-26 Fan deicing or antiicing means Expired - Lifetime US2499831A (en)

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Cited By (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2812899A (en) * 1949-08-30 1957-11-12 A V Roe Canada Ltd Intake sprinkler for gas turbine engines
US5257498A (en) * 1992-04-23 1993-11-02 United Technologies Corporation Efficient anti-ice exhaust vent
WO2006060001A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a tip turbine engine
US20070295011A1 (en) * 2004-12-01 2007-12-27 United Technologies Corporation Regenerative Turbine Blade and Vane Cooling for a Tip Turbine Engine
US20080014078A1 (en) * 2004-12-01 2008-01-17 Suciu Gabriel L Ejector Cooling of Outer Case for Tip Turbine Engine
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
US20080124211A1 (en) * 2004-12-01 2008-05-29 Suciu Gabriel L Diffuser Aspiration For A Tip Turbine Engine
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1099083A (en) * 1910-12-17 1914-06-02 Henry A Duc Jr Self-rotating propeller.
US1344661A (en) * 1915-02-25 1920-06-29 William J H Strong Air machine and propeller
US1728204A (en) * 1927-11-29 1929-09-17 Edge Moor Iron Company Double-flow fan
US1742938A (en) * 1927-09-22 1930-01-07 Alfred G Schumann Propeller for aircraft
DE539730C (en) * 1931-12-01 Babcock & Wilcox Dampfkessel Circulating air heater
US1850378A (en) * 1926-07-23 1932-03-22 Babcock & Wilcox Co Heat exchange device
US2173896A (en) * 1935-11-20 1939-09-26 United Aircraft Corp Blower cooling means for air cooled engines
US2318233A (en) * 1940-02-17 1943-05-04 Escher Wyss Maschf Ag Aircraft propeller
US2347153A (en) * 1942-09-25 1944-04-18 B F Sturtevant Co Engine cooling system

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE539730C (en) * 1931-12-01 Babcock & Wilcox Dampfkessel Circulating air heater
US1099083A (en) * 1910-12-17 1914-06-02 Henry A Duc Jr Self-rotating propeller.
US1344661A (en) * 1915-02-25 1920-06-29 William J H Strong Air machine and propeller
US1850378A (en) * 1926-07-23 1932-03-22 Babcock & Wilcox Co Heat exchange device
US1742938A (en) * 1927-09-22 1930-01-07 Alfred G Schumann Propeller for aircraft
US1728204A (en) * 1927-11-29 1929-09-17 Edge Moor Iron Company Double-flow fan
US2173896A (en) * 1935-11-20 1939-09-26 United Aircraft Corp Blower cooling means for air cooled engines
US2318233A (en) * 1940-02-17 1943-05-04 Escher Wyss Maschf Ag Aircraft propeller
US2347153A (en) * 1942-09-25 1944-04-18 B F Sturtevant Co Engine cooling system

Cited By (63)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2812899A (en) * 1949-08-30 1957-11-12 A V Roe Canada Ltd Intake sprinkler for gas turbine engines
US5257498A (en) * 1992-04-23 1993-11-02 United Technologies Corporation Efficient anti-ice exhaust vent
US5365731A (en) * 1992-04-23 1994-11-22 United Technologies Corporation Efficient anti-ice exhaust method
US20080124211A1 (en) * 2004-12-01 2008-05-29 Suciu Gabriel L Diffuser Aspiration For A Tip Turbine Engine
US20070295011A1 (en) * 2004-12-01 2007-12-27 United Technologies Corporation Regenerative Turbine Blade and Vane Cooling for a Tip Turbine Engine
US20080014078A1 (en) * 2004-12-01 2008-01-17 Suciu Gabriel L Ejector Cooling of Outer Case for Tip Turbine Engine
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
WO2006060001A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a tip turbine engine
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
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US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
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US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
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US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
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US20110142601A1 (en) * 2004-12-01 2011-06-16 Suciu Gabriel L Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US20110200424A1 (en) * 2004-12-01 2011-08-18 Gabriel Suciu Counter-rotating gearbox for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
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US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8672630B2 (en) 2004-12-01 2014-03-18 United Technologies Corporation Annular turbine ring rotor
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine

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