GB2363170A - Attaching a nose cone to a gas turbine engine rotor - Google Patents
Attaching a nose cone to a gas turbine engine rotor Download PDFInfo
- Publication number
- GB2363170A GB2363170A GB0013835A GB0013835A GB2363170A GB 2363170 A GB2363170 A GB 2363170A GB 0013835 A GB0013835 A GB 0013835A GB 0013835 A GB0013835 A GB 0013835A GB 2363170 A GB2363170 A GB 2363170A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- nose cone
- spinner
- gas turbine
- turbine engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/14—Spinners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Abstract
A gas turbine engine rotor and nose cone assembly comprises a conical spinner 40 having a point 42 or dome at an upstream end and a spigot 44 at a downstream end. The spigot 44 has a radially inner cylindrical face 46 removably located against a radially outer cylindrical face 54 of an axially extending flange 52 of a ring 50. The spigot 44 has a radial face 48 removably located against a radial face 56 of the ring 50. The ring 50 is secured to the rotor 24. A plurality of axially extending L-shaped brackets 68 are arranged within the spinner 40 and the axially extending L-shaped brackets are removably secured at a first end to the spinner 40 by generally radially extending countersunk screws 76 and removably secured at a second end to the rotor 24. One embodiment has fan annulus fillers 88 between adjacent fan blades 26 supported by the ring 50, while another embodiment has the spigot (44, fig 4) spaced axially from the downstream end of the spinner. The spinner may be made from a composite material or a lightweight metal, while the rotor may be a fan or compressor rotor. The nose cone assembly has reduced weight, cost and is aerodynamically smoother.
Description
2363170 A GAS TURBINE ENGINE ROTOR AND NOSE CONE ASSEMBLY The present
invention relates to a gas turbine engine rotor and nose cone assembly, particularly for fan rotor and nose cone assembly for a turbofan gas turbine engine.
5 Tde nose cone, sometimes called a spinner, is attached to, and rotates with, a rotor hub in the centre of the inlet of the gas turbine engine. The rotor hub generally carries one or more stages of radially outwardly extending rotor blades. The rotor blades are fan blades, in the case of a 10 turbofan gas turbine engine, or low pressure compressor blades. The nose cone provides an aerodynamic surface covering the upstream end of the rotor hub and directs the inlet airflow smoothly into the hub region of the fan blades, or low-pressure compressor blades.
15 Generally the nose cone has a conical shape with a point at one end and a base portion at the other end. The nose cone is attached to the rotor hub by a number of circumferentially spaced, axially extending, bolts. The bolts are arranged around the base portion of the nose cone 20 and pass through axially aligned apertures in the base portion of the nose cone and the rotor hub and the bolts engage a corresponding number of nuts.
It is known to provide elliptical apertures in the nose cone to allow access to these bolts, for fitting or removing 25 the nose cone. Alternatively it is known to shape the nose cone to provide pockets, or indentations, below the nominal surface of the base portion of the nose cone. The pockets are arranged to be large enough to receive the heads of the bolts.
30 It is also known from our European patent application no. 99309925.8 filed 9 December 1999, which claims priority from our UK patent application no. 9828812.9 filed 29 December 1998 to provide a nose cone assembly comprising a spinner and a fairing. The spinner comprises a conical 35 portion and a cylindrical portion. The conical portion has a point at one end and is secured to the cylindrical portion 2 at the other end. The spinner is attached to the rotor hub by a number of circumferentially spaced, axially extending, bolts. The bolts are arranged around the cylindrical portion of the spinner and pass through axially aligned 5 apertures in a flange on the cylindrical portion of the spinner and the rotor hub and the bolts engage a corresponding number of nuts. A frusto- conical fairing is arranged coaxially with the spinner and covers the cylindrical portion of the spinner. The fairing is attached 10 to the rotor hub by a number of circumferentially spaced brackets. One end of each bracket is secured to the rotor hub by an axially extending bolt and the other end of each bracket is secured to the fairing by a radially extending countersunk screw.
15 A problem with the first two arrangements is that the airflow to the fan blades, over the nose cone, is disturbed in particular at the region surrounding the rotor hub at the root portion of the fan blades. In the first arrangement some of the air flows into the elliptical holes and the 20 sharp edges of the holes affect and disturb the remainder of the airflow passing over them. In the second arrangement the pockets are much larger than the holes and so the pockets affect and disturb the airflow over a larger area of the nose cone. The airflow flows into the pockets and 25 produces eddy currents, which affect the airflow over the nose cone.
In the third arrangement the fairing improves the airflow over the spinner and fairing to the root portion of the fan blades. However, the fairing adds weight to the 30 nose cone assembly because of the use of the spinner and fairing. There is a small step at the interface between the spinner and the fairing, which produces a smaller affect on the airflow over the nose cone assembly. The use of a spinner and fairing is relatively expensive.
Accordingly the present invention seeks to provide a novel gas turbine engine rotor and nose cone assembly which reduces, preferably overcomes, the above mentioned problems.
Accordingly the present invention provides a gas 5 turbine engine rotor and nose cone assembly comprising a rotor and a tapering spinner, the spinner having a point at a first end and a spigot at, or adjacent, a second end, the spigot having a radially inner face removably located against a radially outer face on a hub of the rotor and a 10 radial face removably located against a radial face on the hub of the rotor, means arranged within the spinner to prevent relative axial movement of the spinner and the rotor.
Preferably the means within the spinner comprises 15 axially extending means being arranged within the spinner, the axially extending means being removably secured at a first end to the spinner and removably secured at a second end to the rotor.
Preferably the axially extending means comprises a plurality of circumferentially spaced mounting brackets.
Preferably the mounting brackets are generally Lshaped.
Preferably the nose cone is removably secured to the axially extending means by generally radially inwardly 25 extending fasteners. Preferably the fasteners are screws. Preferably the fasteners are flush with an outer surface of the nose cone. Preferably the fasteners are countersunk screws.
Preferably the axially extending means are secured to 30 the rotor hub by axially extending fasteners. Preferably the fasteners comprise nuts and bolts.
Preferably the spigot is removably located on a ring having an axially extending flange, the ring being secured to the rotor.
Preferably the nose cone comprises a fibre reinforced composite material. Preferably the fibre reinforced 4 composite material comprises carbon, glass or aramid fibres.
Preferably the fibre reinforced composite material comprises a resin matrix.
Preferably the rotor comprises a fan rotor.
5 Preferably the second end of the axially extending means is secured to a flange on the rotor.
The nose cone may be conical or dome shaped.
The present invention will be more fully described by way of example with reference to the accompanying drawings 10 in which: - Figure 1 shows a turbofan gas turbine engine comprising a nose cone assembly according to the present invention.
Figure 2 is an enlarged view of a nose cone assembly shown in figure 1.
15 Figure 3 is a further enlarged view of part of the nose cone assembly shown in figure 2.
Figure 4 is an enlarged view of an alternative embodiment of a nose cone assembly shown in figure 1.
Figure 5 is a perspective view of one of the L-shaped 20 brackets.
A turbofan gas turbine engine 10, as shown in figure 1, comprises in flow series an intake 12, a fan section, 14, a compressor section 16, a combustion section 18, a turbine section 20 and an exhaust 22. The compressor section 16 25 comprises one or more compressors arranged to be driven by one or more turbines in the turbine section 20 via shafts (not shown). The fan section 14 is driven by a turbine in the turbine section 20 via a shaft (not shown) The f an section 14 comprises a fan rotor 24 carrying a plurality of 30 circumferentially spaced radially outwardly extending fan blades 26. The fan rotor 24 and fan blades 26 are surrounded by a fan casing 28 and the fan casing 28 defines the radially outer surface of a fan duct 30. The fan casing 28 is supported from a core engine casing 32 by a plurality 35 of radially extending fan outlet guide vanes 34. The f an duct 30 has an outlet 36.
The gas turbine engine 10 operates quite conventionally in that air enters the intake 12 and is initially compressed by the fan section 14. A portion of the air flows through the fan duct 30 and the outlet 36 to provide thrust. The 5 remainder of the air is compressed by the compressor section 16 and is supplied to the combustion section 18. Fuel is supplied to the combustion section 18 and is burnt in the air to produce hot gases. The hot gases flow through, and drive, the turbine section 20 and then flow through the 10 exhaust 22. The turbine section 20 in turn drives the fan section 14 and the compressor section 16.
The fan section 14 and in particular the fan rotor 24 and nose cone assembly 124 are shown more clearly in figures 2 and 3. The nose cone assembly 124 comprises a conical 15 spinner 40, which is removably secured to the upstream end of the fan rotor 24. The conical spinner comprises a point, a vertex, 42 at its upstream end and a spigot 44 at its downstream end. The spigot 44 has a radially inner cylindrical face 46 and a radial face 48 at its downstream 20 end facing in a downstream direction. The radially inner cylindrical face 46 of the spigot 44 is removably located and abuts against the radially outer cylindrical face 54 of an axially upstream extending flange 52 on a ring 50. The inner cylindrical face 46 of the spigot 44 and the outer 25 face 54 of the flange 52 have substantially the same diameter. The radial face 48 is removably located and abuts against a radial face 56 facing in an upstream direction on the ring 50.
The ring 50 is secured to a radially extending flange 30 58 on the fan rotor 24 by a plurality of axially extending bolts 60, which extend through axially aligned apertures 64 and 66 in the ring 50 and flange 58 respectively and, which engage a corresponding number of nuts 62.
A plurality of axially extending L-shaped brackets 68 35 are arranged radially within the spinner 40. The axially extending L- shaped brackets 68 are removably secured at 6 their upstream ends 70 to the spinner 40 and the axially extending L- shaped brackets 68 are removably secured at their downstream ends 72 to the fan rotor 24. The axially extending L-shaped brackets 68 comprise flexible spring 5 metal finger members, which are bent to produce the L- shape.
The axially extending brackets 68 abut the conical inner surface 74 of the spinner 40 and the radially inner surface 55 of the flange 52 so that the spinner 40 and the flange 52 provide radial support for the axially extending 10 brackets 68 in operation. The upstream ends 70 of the axially extending L-shaped brackets 68 are secured to the spinner 40 by a respective one of a plurality of countersunk screws 76. Each countersunk screw 76 extends generally radially through a respective one of a plurality of 15 countersunk apertures 78 and a respective one of a plurality of apertures 80 in the spinner 40 and axially extending Lshaped brackets 68 respectively to engage a respective one of a plurality of nuts 82. The heads of the countersunk screws 76 lie substantially flush with the outer conical 20 surface 84 of the spinner 40. The spinner 40 has a protective coating 85 of polyurethane, or other suitable material, to reduce erosion of the spinner 40 due to impact of foreign bodies, for example dirt, grit etc. Each countersunk aperture 78 has a respective one of a plurality 25 of conical washers 87. Each conical washer 87 is placed coaxially in the respective countersunk aperture 78. The rims of the washers 87 overlap the protective coating 85. The countersunk screws 76 abut the conical washers 87 and the washers protect the spinner 40. The nuts 82 are 30 retained in baskets, or otherwise, secured to the axially extending L- shaped brackets 68.
The downstream ends 72 of the axially extending Lshaped brackets 68 abut the ring 50. The downstream ends 72 of the axially extending L-shaped brackets 68 are secured to 35 the ring 50 and the radially extending flange 58 on the fan rotor 24 by the bolts 60. The bolts 60 extend through 7 axially aligned apertures 64, 66 and 86 in the ring 50, the flange 58 and the axially extending L-shaped brackets 68 and, which engage the nuts 62.
The upstream end 42 of the spinner 40 comprises a 5 rubber point, or tip.
A plurality of fan annulus fillers 88 are provided and each fan annulus filler 88 is arranged circumferentially between two adjacent fan blades 26 to define a portion of the inner surface of the flow path through the fan duct 30.
10 The fan annulus fillers 88 have hook shaped roots 90, which engage corresponding hook shaped features on the fan rotor 24. The upstream ends 92 of the fan annulus fillers 88 abut the ring 50 so that the ring 50 retains the fan annulus fillers 88 axially in position and radially supports the is upstream ends of the annulus fillers 88.
The spinner 40 preferably comprises a single piece fibre reinforced composite material, preferably the composite material comprises glass, aramid or carbon fibres and preferably the composite material comprises a resin 20 matrix. A portion 45 of the spigot 44 may comprise a low density core, for example a honeycomb core, surrounded by the fibre reinforced composite material to reduce the weight of the spinner 40. Alternatively the spinner may be manufactured from a lightweight metal, or alloy, for example 25 titanium, aluminium, a titanium alloy or an aluminium alloy.
In operation the spigot 44, with its cylindrical inner face 46 having the same diameter as the cylindrical outer face 54 of the flange 52 on the ring 50, ensures that the spinner 40 is coaxial with the fan rotor 24 to prevent 30 vibration of the fan rotor 24 and nose cone assembly. The radial face 48 of the spigot 44 transmits any bird strike loads to the radial face 56 of the ring 50 and then to the fan rotor 24 and provides the axial location. The single piece spinner 40 defines an aerodynamically smooth outer 35 conical surface 84 from the point 42 to the fan blades 26 substantially without any indentations, pockets or apertures 8 in the conical surface 84 and without any fasteners projecting from the conical surface 84 into the airflow to disturb the airflow over the nose cone 40. The countersunk screws 76 fit in countersunk apertures 78 in the spinner 40 5 and lie substantially flush with the outer surface 84 of the spinner 40 and do not affect the airflow over the spinner 40.
The spinner 40 is removed, to allow access to the fan rotor 24 for removal and replacement of fan blades 26 etc., 10 by firstly unthreading the countersunk screws 76 from the nuts 82. The spinner 40 is then pulled to disengage the spigot 44 from the axially extending flange 52 on the ring 50. The spinner 40 may be provided with apertures at diametrically opposite positions to allow the insertion of 15 tools to apply a load to remove the spinner 40. The axially extending L-shaped brackets 68 and the ring 50 are then removed by unthreading the bolts 60 from the nuts 62to allow access to the fan blades 26 and fan annulus fillers 88.
20 The advantages of the present invention compared to our previous European patent application no. 99309925.8 are firstly that the nose cone assembly is cheaper because there is no separate fairing. Secondly the weight of the nose cone assembly is reduced because there is no separate 25 fairing. Thirdly the aerodynamics are improved because the removal of the fairing removes the annular step at the point where the leading edge of the fairing abuts the spinner.
Fourthly the spigot abutments transmit any bird strike loads whereas the axially extending brackets had to transmit some 30 of the bird strike loads. The axially extending brackets only prevent axial upstream movement of the spinner. Additionally the requirement for a seal between the spinner and fairing and the retention of the seal is removed. Also the build up of ice at the interface between the upstream 35 end of the fairing and the spinner is eliminated and vibration of the fairing is eliminated.
A further fan rotor 24 and nose cone assembly 126 according to the present invention is shown in figures 4 and 5, and like parts are denoted by like numbers. The embodiment in figures 4 and 5 shows the baskets 100 to 5 retain the nuts 82. The embodiment in figure 4 differs in that the ring 50 is generally L-shaped, rather than being purely radial and the flange 52 extends in an axially downstream direction rather than an upstream direction. The embodiment in figures 4 and 5 also differs in that the 10 spigot 44 is spaced axially from the downstream end of the spinner 40. The embodiment in figures 4 and 5 also differs in that there are no annulus fillers between the fan blades.
The hub of the fan rotor 24 defines the portion of the inner surface of the flow path through the fan duct 30. Two 15 dowels 102 are provided to locate the downstream end 72 of each L-shaped bracket 68 on the thrust ring 50 so that the aperture 80 in the upstream end 70 of the bracket 68 is aligned correctly with the corresponding aperture 78 in the spinner 40.
20 The invention has been described with reference to the locating of the spinner to a ring and the securing of the axially extending L-shaped brackets to the ring. It may be possible to locate the spinner directly against the fan rotor and to secure the axially extending L-shaped brackets 25 directly to the fan rotor.
Although the invention has been described with reference to a fan rotor the invention is equally applicable to a compressor rotor.
Although the invention has been described with 30 reference to a plurality of axially extending L-shaped brackets, it may be possible to use other axially extending means to secure the spinner to the rotor. It may be possible to use other means within the spinner to prevent relative axial movement between the spinner and the rotor.
35 Although the invention has been described with reference to the use of common fasteners to fasten the ring and the axially extending L-shaped brackets to the fan rotor it may be possible to use separate fasteners for the thrust ring and separate fasteners for the L-shaped brackets.
The spinner may have any other suitable tapering shape 5 f or example a curved shape, a domed shape, rather than a purely conical shape and the spinner is axis-symmetric.
Claims (19)
1. A gas turbine engine rotor and nose cone assembly comprising a rotor and a tapering spinner, the spinner having a point at a first end and a spigot at, or adjacent, 5 a second end, the spigot having a radially inner face removably located against a radially outer face on a hub of the rotor and a radial face removably located against a radial face on the hub of the rotor, means arranged within the spinner to prevent relative axial movement of the 10 spinner and the rotor.
2. A gas turbine engine rotor and nose cone assembly as claimed in claim 1 wherein the means within the spinner comprises axially extending means being arranged within the spinner, the axially extending means being removably secured 15 at a first end to the spinner and removably secured at a second end to the rotor.
3. A gas turbine engine rotor and nose cone assembly as claimed in claim 2 wherein the axially extending means comprises a plurality of circumferentially spaced mounting 20 brackets.
4. A gas turbine engine rotor and nose cone assembly as claimed in claim 3 wherein the mounting brackets are generally L-shaped.
5. A gas turbine engine rotor and nose cone assembly as 25 claimed in claim 2, claim 3 or claim 4 wherein the spinner is removably secured to the axially extending means by generally radially inwardly extending fasteners.
6. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 2 to 5 wherein the fasteners are 30 screws.
7. A gas turbine engine rotor and nose cone assembly as claimed in claim 5 or claim 6 wherein the fasteners are substantially flush with an outer surface of the spinner.
8. A gas turbine engine rotor and nose cone assembly as claimed in claim 5, claim 6 or claim 7 wherein the fasteners are countersunk screws.
9. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 2 to 8 wherein the axially extending means are secured to the rotor by axially extending fasteners.
5
10. A gas turbine engine rotor and nose cone assembly as claimed in claim 9 wherein the fasteners comprise nuts and bolts.
11. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 1 to 10 wherein the spigot is 10 removably located on a ring having an axially extending flange, the ring being secured to the rotor.
12. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 1 to 11 wherein the spinner comprises a fibre reinforced composite material.
15
13. A gas turbine engine rotor and nose cone assembly as claimed in claim 12 wherein the fibre reinforced composite material comprises carbon, glass or aramid fibres.
14. A gas turbine engine rotor and nose cone assembly as claimed in claim 12 or claim 13 wherein the fibre reinforced composite material comprises a resin matrix.
15. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 1 to 14 wherein the rotor comprises a fan rotor.
16. A gas turbine engine rotor and nose cone assembly as claimed in claim 2 wherein the second end of the axially extending means is secured to a flange on the rotor.
17. A gas turbine engine rotor and nose cone assembly as claimed in any of claims 1 to 16 wherein the spinner is conical or dome shaped.
30
18. A gas turbine engine rotor and nose cone assembly substantially as hereinbefore described with reference to figures 1, 2 and 3 of the accompanying drawings.
19. A gas turbine engine rotor and nose cone assembly substantially as hereinbefore described with reference to 35 figures 1, 4 and 5 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0013835A GB2363170A (en) | 2000-06-08 | 2000-06-08 | Attaching a nose cone to a gas turbine engine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0013835A GB2363170A (en) | 2000-06-08 | 2000-06-08 | Attaching a nose cone to a gas turbine engine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0013835D0 GB0013835D0 (en) | 2000-07-26 |
| GB2363170A true GB2363170A (en) | 2001-12-12 |
Family
ID=9893140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0013835A Withdrawn GB2363170A (en) | 2000-06-08 | 2000-06-08 | Attaching a nose cone to a gas turbine engine rotor |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2363170A (en) |
Cited By (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002020349A1 (en) * | 2000-09-07 | 2002-03-14 | Honeywell International Inc. | Two piece spinner |
| GB2426792A (en) * | 2005-04-01 | 2006-12-06 | David Richard Hopkins | Fan with conical hub |
| FR2908827A1 (en) * | 2006-11-16 | 2008-05-23 | Snecma Sa | Turbine engine i.e. turbo jet engine, spinner for aircraft, has groove sealing ring including outer surface aligned with outer surface of spinner, and threaded surface formed in direction inverse to rotational direction of fan blade |
| US20100051112A1 (en) * | 2008-09-03 | 2010-03-04 | Rolls-Royce Deutschland Ltd & Co Kg | Intake cone for a gas-turbine engine |
| DE102009016802A1 (en) * | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Fiber composite inlet cone for a gas turbine engine |
| GB2474449A (en) * | 2009-10-14 | 2011-04-20 | Rolls Royce Plc | Annulus filler with connection for nose cone |
| EP2369155A2 (en) | 2010-03-26 | 2011-09-28 | Rolls-Royce plc | A gas turbine engine nose cone |
| DE102010062125A1 (en) * | 2010-11-29 | 2012-05-31 | Rolls-Royce Deutschland Ltd & Co Kg | A method of removing the polyurethane coating from a composite nose cone of a jet engine |
| CN102562306A (en) * | 2010-11-30 | 2012-07-11 | 劳斯莱斯有限公司 | Nose cone assembly |
| US8322991B2 (en) | 2009-04-10 | 2012-12-04 | Rolls-Royce Corporation | Balance weight |
| US8425197B2 (en) | 2009-02-24 | 2013-04-23 | Rolls-Royce Plc | Mounting arrangement |
| US8529204B2 (en) | 2008-02-26 | 2013-09-10 | Rolls-Royce Plc | Gas turbine engine having a nose cone assembly rigidly attached in an axial direction but flexible in a radial direction |
| US8616854B2 (en) | 2009-03-05 | 2013-12-31 | Rolls-Royce Corporation | Nose cone assembly |
| DE102009053000B4 (en) * | 2009-11-16 | 2014-01-02 | Rolls-Royce Deutschland Ltd & Co Kg | Fan retaining disc for a jet engine |
| EP2915953A1 (en) | 2014-03-03 | 2015-09-09 | Rolls-Royce Corporation | Spinner for a gas turbine engine |
| CN104968892A (en) * | 2013-02-08 | 2015-10-07 | 通用电气公司 | Hybrid spinner support |
| US9200595B2 (en) | 2010-11-30 | 2015-12-01 | Rolls-Royce Plc | Nose cone assembly |
| EP2993305A1 (en) | 2014-09-08 | 2016-03-09 | Rolls-Royce Deutschland Ltd & Co KG | Panels of a fan of a gas turbine |
| EP2998515A1 (en) | 2014-09-08 | 2016-03-23 | Rolls-Royce Deutschland Ltd & Co KG | Filling elements of a fan of a gas turbine |
| JP2017078413A (en) * | 2015-10-19 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | Aircraft engine spinner improved in crosswind performance |
| US9879698B2 (en) | 2015-10-26 | 2018-01-30 | Rolls-Royce North American Technologies Inc. | Nose cone and shaft balancing assembly |
| US10024234B2 (en) | 2014-09-08 | 2018-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Panels of a fan of a gas turbine |
| EP3348785A1 (en) * | 2017-01-13 | 2018-07-18 | United Technologies Corporation | Anti-rotation lock for threaded in place nosecone or spinner |
| CN109339955A (en) * | 2018-12-16 | 2019-02-15 | 中国航发沈阳发动机研究所 | A kind of support construction of air bleed valve regulating mechanism |
| US10583913B2 (en) | 2017-03-14 | 2020-03-10 | General Electric Company | Stud push out mount for a turbine engine spinner assembly having a spinner push out stud joint connecting through a counterbore of a spinner bolt hole |
| US10612405B2 (en) | 2017-01-13 | 2020-04-07 | United Technologies Corporation | Stator outer platform sealing and retainer |
| FR3089548A1 (en) * | 2018-12-07 | 2020-06-12 | Safran Aircraft Engines | BLOWER COMPRISING AN INTER-BLADE PLATFORM FIXED UPWARD BY A RUBBER |
| EP3750798A1 (en) * | 2017-07-13 | 2020-12-16 | Ratier-Figeac SAS | Protection of propeller components |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2371801A (en) * | 1943-08-18 | 1945-03-20 | Arthur C Chester | Propeller spinner attaching device |
| GB650956A (en) * | 1947-12-16 | 1951-03-07 | Stanley Ronald Mitchinson | Improvements in or relating to model aircraft propeller spinners |
| US3990814A (en) * | 1975-06-25 | 1976-11-09 | United Technologies Corporation | Spinner |
| US4863354A (en) * | 1987-10-07 | 1989-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Nose cowl for a turbojet engine shaft |
| EP0850831A2 (en) * | 1996-12-24 | 1998-07-01 | United Technologies Corporation | Inlet nose cone assembly and method for repairing the assembly |
-
2000
- 2000-06-08 GB GB0013835A patent/GB2363170A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2371801A (en) * | 1943-08-18 | 1945-03-20 | Arthur C Chester | Propeller spinner attaching device |
| GB650956A (en) * | 1947-12-16 | 1951-03-07 | Stanley Ronald Mitchinson | Improvements in or relating to model aircraft propeller spinners |
| US3990814A (en) * | 1975-06-25 | 1976-11-09 | United Technologies Corporation | Spinner |
| US4863354A (en) * | 1987-10-07 | 1989-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Nose cowl for a turbojet engine shaft |
| EP0850831A2 (en) * | 1996-12-24 | 1998-07-01 | United Technologies Corporation | Inlet nose cone assembly and method for repairing the assembly |
Cited By (56)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002020349A1 (en) * | 2000-09-07 | 2002-03-14 | Honeywell International Inc. | Two piece spinner |
| GB2426792A (en) * | 2005-04-01 | 2006-12-06 | David Richard Hopkins | Fan with conical hub |
| GB2426792B (en) * | 2005-04-01 | 2007-06-27 | David Richard Hopkins | A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system |
| FR2908827A1 (en) * | 2006-11-16 | 2008-05-23 | Snecma Sa | Turbine engine i.e. turbo jet engine, spinner for aircraft, has groove sealing ring including outer surface aligned with outer surface of spinner, and threaded surface formed in direction inverse to rotational direction of fan blade |
| US8529204B2 (en) | 2008-02-26 | 2013-09-10 | Rolls-Royce Plc | Gas turbine engine having a nose cone assembly rigidly attached in an axial direction but flexible in a radial direction |
| US8678772B2 (en) | 2008-09-03 | 2014-03-25 | Rolls-Royce Deutschland Ltd & Co Kg | Intake cone for a gas-turbine engine |
| US20100051112A1 (en) * | 2008-09-03 | 2010-03-04 | Rolls-Royce Deutschland Ltd & Co Kg | Intake cone for a gas-turbine engine |
| EP2161431A3 (en) * | 2008-09-03 | 2013-02-27 | Rolls-Royce Deutschland Ltd & Co KG | Inlet nose cone for an aircraft gas turbine powerplant |
| EP2221247A3 (en) * | 2009-02-24 | 2014-02-26 | Rolls-Royce Plc | Mounting arrangement for a nose cone of a gas turbine engine |
| US8425197B2 (en) | 2009-02-24 | 2013-04-23 | Rolls-Royce Plc | Mounting arrangement |
| US8616854B2 (en) | 2009-03-05 | 2013-12-31 | Rolls-Royce Corporation | Nose cone assembly |
| US8540492B2 (en) * | 2009-04-09 | 2013-09-24 | Rolls-Royce Deutschland Ltd & Co Kg | Intake cone in a fiber compound material for a gas-turbine engine |
| US20100258199A1 (en) * | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Intake cone in a fiber compound material for a gas-turbine engine |
| DE102009016802A1 (en) * | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Fiber composite inlet cone for a gas turbine engine |
| EP2241738A1 (en) * | 2009-04-09 | 2010-10-20 | Rolls-Royce Deutschland Ltd & Co KG | Inlet cone made of compound fibre material for a gas turbine engine |
| US8322991B2 (en) | 2009-04-10 | 2012-12-04 | Rolls-Royce Corporation | Balance weight |
| GB2474449B (en) * | 2009-10-14 | 2012-02-22 | Rolls Royce Plc | Annulus filler element for a rotor of a turbomachine |
| US8858180B2 (en) | 2009-10-14 | 2014-10-14 | Rolls-Royce Plc | Annulus filler element for a rotor of a turbomachine |
| GB2474449A (en) * | 2009-10-14 | 2011-04-20 | Rolls Royce Plc | Annulus filler with connection for nose cone |
| DE102009053000B4 (en) * | 2009-11-16 | 2014-01-02 | Rolls-Royce Deutschland Ltd & Co Kg | Fan retaining disc for a jet engine |
| CN102200055A (en) * | 2010-03-26 | 2011-09-28 | 劳斯莱斯有限公司 | A gas turbine engine nose cone |
| CN102200055B (en) * | 2010-03-26 | 2015-04-22 | 劳斯莱斯有限公司 | A gas turbine engine nose cone |
| EP2369155A2 (en) | 2010-03-26 | 2011-09-28 | Rolls-Royce plc | A gas turbine engine nose cone |
| WO2012072589A1 (en) * | 2010-11-29 | 2012-06-07 | Rolls-Royce Deutschland Ltd & Co Kg | Method for stripping the polyurethane coating from a composite-material nose cone of a jet engine by using a gas laser |
| DE102010062125A1 (en) * | 2010-11-29 | 2012-05-31 | Rolls-Royce Deutschland Ltd & Co Kg | A method of removing the polyurethane coating from a composite nose cone of a jet engine |
| CN102562306A (en) * | 2010-11-30 | 2012-07-11 | 劳斯莱斯有限公司 | Nose cone assembly |
| US9410431B2 (en) | 2010-11-30 | 2016-08-09 | Rolls-Royce Plc | Nose cone assembly |
| US10669934B2 (en) | 2010-11-30 | 2020-06-02 | Rolls-Royce Plc | Nose cone assembly |
| US9200595B2 (en) | 2010-11-30 | 2015-12-01 | Rolls-Royce Plc | Nose cone assembly |
| EP2458175A3 (en) * | 2010-11-30 | 2018-02-21 | Rolls-Royce plc | Nose cone assembly |
| CN102562306B (en) * | 2010-11-30 | 2016-03-09 | 劳斯莱斯有限公司 | Nose-cone assembly |
| CN104968892A (en) * | 2013-02-08 | 2015-10-07 | 通用电气公司 | Hybrid spinner support |
| CN104968892B (en) * | 2013-02-08 | 2017-12-05 | 通用电气公司 | Hybrid propeller boss lid support |
| US9969489B2 (en) | 2013-02-08 | 2018-05-15 | General Electric Company | Hybrid spinner support |
| JP2016515176A (en) * | 2013-02-08 | 2016-05-26 | ゼネラル・エレクトリック・カンパニイ | Hybrid spinner support |
| US10100644B2 (en) | 2014-03-03 | 2018-10-16 | Rolls-Royce Corporation | Spinner for a gas turbine engine |
| EP2915953A1 (en) | 2014-03-03 | 2015-09-09 | Rolls-Royce Corporation | Spinner for a gas turbine engine |
| EP2998515A1 (en) | 2014-09-08 | 2016-03-23 | Rolls-Royce Deutschland Ltd & Co KG | Filling elements of a fan of a gas turbine |
| DE102014217887A1 (en) | 2014-09-08 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Filling elements of a fan of a gas turbine |
| US9664069B2 (en) | 2014-09-08 | 2017-05-30 | Rolls-Royce Deutschland Ltd & Co Kg | Panels of a fan of a gas turbine |
| EP2993305A1 (en) | 2014-09-08 | 2016-03-09 | Rolls-Royce Deutschland Ltd & Co KG | Panels of a fan of a gas turbine |
| DE102014217884A1 (en) | 2014-09-08 | 2016-03-24 | Rolls-Royce Deutschland Ltd & Co Kg | Filling elements of a fan of a gas turbine |
| US10024234B2 (en) | 2014-09-08 | 2018-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Panels of a fan of a gas turbine |
| US10167088B2 (en) | 2015-10-19 | 2019-01-01 | General Electric Company | Crosswind performance aircraft engine spinner |
| JP2017078413A (en) * | 2015-10-19 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | Aircraft engine spinner improved in crosswind performance |
| US9879698B2 (en) | 2015-10-26 | 2018-01-30 | Rolls-Royce North American Technologies Inc. | Nose cone and shaft balancing assembly |
| EP3348785A1 (en) * | 2017-01-13 | 2018-07-18 | United Technologies Corporation | Anti-rotation lock for threaded in place nosecone or spinner |
| US11560811B2 (en) | 2017-01-13 | 2023-01-24 | Raytheon Technologies Corporation | Stator outer platform sealing and retainer |
| US10330009B2 (en) | 2017-01-13 | 2019-06-25 | United Technologies Corporation | Lock for threaded in place nosecone or spinner |
| US10612405B2 (en) | 2017-01-13 | 2020-04-07 | United Technologies Corporation | Stator outer platform sealing and retainer |
| US10583913B2 (en) | 2017-03-14 | 2020-03-10 | General Electric Company | Stud push out mount for a turbine engine spinner assembly having a spinner push out stud joint connecting through a counterbore of a spinner bolt hole |
| EP3750798A1 (en) * | 2017-07-13 | 2020-12-16 | Ratier-Figeac SAS | Protection of propeller components |
| FR3089548A1 (en) * | 2018-12-07 | 2020-06-12 | Safran Aircraft Engines | BLOWER COMPRISING AN INTER-BLADE PLATFORM FIXED UPWARD BY A RUBBER |
| US11162418B2 (en) | 2018-12-07 | 2021-11-02 | Safran Aircraft Engines | Fan comprising an inter-blade platform attached upstream by a ferrule |
| CN109339955B (en) * | 2018-12-16 | 2021-09-03 | 中国航发沈阳发动机研究所 | Supporting structure of deflation valve adjusting mechanism |
| CN109339955A (en) * | 2018-12-16 | 2019-02-15 | 中国航发沈阳发动机研究所 | A kind of support construction of air bleed valve regulating mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0013835D0 (en) | 2000-07-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB2363170A (en) | Attaching a nose cone to a gas turbine engine rotor | |
| EP1227036B1 (en) | A gas turbine engine nose cone | |
| EP1016588B1 (en) | Gas turbine nose cone assembly | |
| US8529204B2 (en) | Gas turbine engine having a nose cone assembly rigidly attached in an axial direction but flexible in a radial direction | |
| US6942462B2 (en) | Gas turbine engine nose cone | |
| EP3450726B1 (en) | Gas turbine engine | |
| EP3450727B1 (en) | Gas turbine engine | |
| US8616854B2 (en) | Nose cone assembly | |
| CA2680629C (en) | Integrated guide vane assembly | |
| JP4495335B2 (en) | Periodic stator airfoil | |
| US6371721B1 (en) | Gas turbine engine blade containment assembly | |
| US20080159856A1 (en) | Guide vane and method of fabricating the same | |
| GB2361747A (en) | Fan casing with radially movable liner | |
| US10954798B2 (en) | Gas turbine engine with optimized fan blade geometry | |
| US6394746B1 (en) | Gas turbine engine blade containment assembly | |
| CN110382841B (en) | Protected core portal | |
| GB2364748A (en) | Gas turbine engine nose cone with tool access hole plug/cover | |
| EP3269961B1 (en) | Nose cone attachment for turbofan engine | |
| US20130052026A1 (en) | Axial retention system for a bladed rotor with multiple blade types | |
| CA2845615C (en) | Tip-controlled integrally bladed rotor for gas turbine engine | |
| US10309224B2 (en) | Split ring spring dampers for gas turbine rotor assemblies | |
| US10557412B2 (en) | Systems for reducing deflection of a shroud that retains fan exit stators | |
| CA2025244A1 (en) | Bolt shield for rotating exhaust duct | |
| US20200063604A1 (en) | Gas turbine engine | |
| US20200165939A1 (en) | Windage shield |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |