EP2775104B1 - Conformal liner for gas turbine engine fan section - Google Patents
Conformal liner for gas turbine engine fan section Download PDFInfo
- Publication number
- EP2775104B1 EP2775104B1 EP14158310.4A EP14158310A EP2775104B1 EP 2775104 B1 EP2775104 B1 EP 2775104B1 EP 14158310 A EP14158310 A EP 14158310A EP 2775104 B1 EP2775104 B1 EP 2775104B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fan case
- liner
- case structure
- thermal expansion
- composite
- 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.)
- Active
Links
- 239000002131 composite material Substances 0.000 claims description 15
- 239000000853 adhesive Substances 0.000 claims description 10
- 230000001070 adhesive effect Effects 0.000 claims description 10
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 229920005989 resin Polymers 0.000 claims description 4
- 239000011347 resin Substances 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000011152 fibreglass Substances 0.000 claims description 3
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 239000004945 silicone rubber Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/231—Preventing heat transfer
Definitions
- This disclosure relates to a fan case structure for a gas turbine engine, and, in particular, a conformal liner for the fan case structure.
- One type of gas turbine engine includes a core engine having compressor and turbine sections that drive a fan section.
- the fan section includes circumferentially arranged fan blades disposed within a fan case.
- the fan section is subject to large temperature fluctuations throughout engine operation. A minimized clearance tight seal is desired between the tips of the fan blades and the fan case throughout engine operation at the various operating temperatures.
- the composite fan case structure includes a structure constructed from resin and at least one of carbon fibers and fiberglass.
- the liner is an aluminum alloy.
- the adhesive is silicone rubber.
- a rub strip is supported radially inward from and by the liner.
- the composite fan case structure includes a composite septum interconnecting the adhesive to a honeycomb structure that is supported by and radially inward from a composite fan case.
- FIG. 1 An example gas turbine engine 10 is schematically illustrated in Figure 1 .
- the gas turbine engine 10 includes a compressor section 12, a combustor section 14 and a turbine section 16, which are arranged within a core housing 24.
- high pressure stages of the compressor section 12 and the turbine section 16 are mounted on a first shaft 20, which is rotatable about an axis A.
- Low pressure stages of the compressor section 12 and turbine section 16 are mounted on a second shaft 22 which is coaxial with the first shaft 20 and rotatable about the axis A.
- the first and second shafts 20, 22 are supported for rotation within the core housing 24.
- a fan section 18 is arranged within a fan case structure 30, which provides a bypass flow path 28 between the fan case structure 30 and the core housing 24.
- the first shaft 20 rotationally drives circumferentially arranged fan blades 26 that provide flow through the bypass flow path 28.
- the fan blades 26 are constructed from an aluminum alloy. It should be understood that the configuration illustrated in Figure 1 is exemplary only, and the disclosure may be used in other configurations. Although a high bypass engine is illustrated, it should be understood that the disclosure also relates to other types of gas turbine engines, such as turbo jets.
- the fan section 18 includes a fan case structure 30 comprising multiple components in one example.
- a honeycomb structure 40 which may be constructed from aluminum, is supported radially inward from and on the fan case 32.
- a septum 42 is arranged radially inward from and supported by the honeycomb structure 40.
- the fan case structure 30 includes a composite fan case 32, which is constructed from carbon fiber and resin in one example.
- the septum 42 is a composite structure constructed from fiberglass and resin. As can be appreciated, composite structures have relatively low coefficients of thermal expansion and are dimensionally stable throughout the various operating temperatures.
- a continuous, ring-shaped liner 44 which is an aluminum alloy, for example, is supported by the fan case structure 30, and in the example shown, by the septum 42, using an elastomeric adhesive 46.
- the adhesive 44 has a room temperature radial thickness 48 of 0.100 in. (2.54 mm) and greater than 300% elongation, which may be provided by a silicone rubber.
- the liner 44 has a coefficient of thermal expansion that is substantially the same as the coefficient of thermal expansion of the fan blades 26 and substantially different than the fan case structure 30.
- the fan blades 26 and liner 44 have coefficients of thermal expansion that are within 1 x 10- 6 /°F (1.8 x 10 -6 /°C) of one another and are constructed from the same series aluminum alloy, which may be AM54027 in one example.
- the liner coefficient of thermal expansion is greater than the fan case structure thermal expansion by at least 10 x 10 -6 /°F (18 x 10- 6 /°C)
- the liner 44 includes a rub strip 36 that provides an abradable material immediately adjacent to tips 34 of the fan blades 26, providing a blade tip clearance 38. It is desirable to maintain a desired radial blade tip clearance throughout various fan section operating temperatures. In one example, a desired radial tip clearance is about 0.030 in. at -65°F (0.76 mm at -54°C) ambient, which is typically encountered during cruise altitude.
- the elastomeric adhesive 46 is selected to accommodate changes in a diameter 50 (only radial lead line is shown in Figure 3 ) of the liner 44 as the liner 44 expand and contract during operation.
Description
- This disclosure relates to a fan case structure for a gas turbine engine, and, in particular, a conformal liner for the fan case structure.
- One type of gas turbine engine includes a core engine having compressor and turbine sections that drive a fan section. The fan section includes circumferentially arranged fan blades disposed within a fan case. The fan section is subject to large temperature fluctuations throughout engine operation. A minimized clearance tight seal is desired between the tips of the fan blades and the fan case throughout engine operation at the various operating temperatures.
- One system has been proposed to accommodate thermal expansion and contraction in a fan section having composite fan blades. The composite fan blades are arranged within a composite liner of generally the same material. Several pins at discrete circumferential locations along the liner are used to support the liner relative to a metallic fan case and an example is show in the patent application
GB-2361747 - According to the present invention, there is provided a fan case structure, as claimed in claim 1.
- In an embodiment, the composite fan case structure includes a structure constructed from resin and at least one of carbon fibers and fiberglass. The liner is an aluminum alloy.
- In a further embodiment of any of the above, the adhesive is silicone rubber.
- In a further embodiment of any of the above, a rub strip is supported radially inward from and by the liner. The composite fan case structure includes a composite septum interconnecting the adhesive to a honeycomb structure that is supported by and radially inward from a composite fan case.
- The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
-
Figure 1 is a schematic, cross-sectional side view of an example gas turbine engine. -
Figure 2 is an enlarged, cross-sectional side view of a fan case structure in a fan section of the gas turbine engine shown inFigure 1 . -
Figure 3 is a further enlarged view of the fan case structure shown inFigure 2 . -
Figure 4 is a schematic, cross-sectional end view to the fan section. - An example
gas turbine engine 10 is schematically illustrated inFigure 1 . Thegas turbine engine 10 includes acompressor section 12, acombustor section 14 and aturbine section 16, which are arranged within acore housing 24. In the example illustrated, high pressure stages of thecompressor section 12 and theturbine section 16 are mounted on afirst shaft 20, which is rotatable about an axis A. Low pressure stages of thecompressor section 12 andturbine section 16 are mounted on asecond shaft 22 which is coaxial with thefirst shaft 20 and rotatable about the axis A. The first andsecond shafts core housing 24. - A
fan section 18 is arranged within afan case structure 30, which provides abypass flow path 28 between thefan case structure 30 and thecore housing 24. In the example illustrated, thefirst shaft 20 rotationally drives circumferentially arrangedfan blades 26 that provide flow through thebypass flow path 28. In one example, thefan blades 26 are constructed from an aluminum alloy. It should be understood that the configuration illustrated inFigure 1 is exemplary only, and the disclosure may be used in other configurations. Although a high bypass engine is illustrated, it should be understood that the disclosure also relates to other types of gas turbine engines, such as turbo jets. - Referring to
Figures 2-4 , thefan section 18 includes afan case structure 30 comprising multiple components in one example. Ahoneycomb structure 40, which may be constructed from aluminum, is supported radially inward from and on thefan case 32. Aseptum 42 is arranged radially inward from and supported by thehoneycomb structure 40. - In one example, the
fan case structure 30 includes acomposite fan case 32, which is constructed from carbon fiber and resin in one example. In one example, theseptum 42 is a composite structure constructed from fiberglass and resin. As can be appreciated, composite structures have relatively low coefficients of thermal expansion and are dimensionally stable throughout the various operating temperatures. - A continuous, ring-
shaped liner 44, which is an aluminum alloy, for example, is supported by thefan case structure 30, and in the example shown, by theseptum 42, using anelastomeric adhesive 46. In one example, theadhesive 44 has a room temperatureradial thickness 48 of 0.100 in. (2.54 mm) and greater than 300% elongation, which may be provided by a silicone rubber. - The
liner 44 has a coefficient of thermal expansion that is substantially the same as the coefficient of thermal expansion of thefan blades 26 and substantially different than thefan case structure 30. In one example, thefan blades 26 andliner 44 have coefficients of thermal expansion that are within 1 x 10-6/°F (1.8 x 10-6/°C) of one another and are constructed from the same series aluminum alloy, which may be AM54027 in one example. The liner coefficient of thermal expansion is greater than the fan case structure thermal expansion by at least 10 x 10-6/°F (18 x 10-6/°C) - The
liner 44 includes arub strip 36 that provides an abradable material immediately adjacent totips 34 of thefan blades 26, providing ablade tip clearance 38. It is desirable to maintain a desired radial blade tip clearance throughout various fan section operating temperatures. In one example, a desired radial tip clearance is about 0.030 in. at -65°F (0.76 mm at -54°C) ambient, which is typically encountered during cruise altitude. Thus, theelastomeric adhesive 46 is selected to accommodate changes in a diameter 50 (only radial lead line is shown inFigure 3 ) of theliner 44 as theliner 44 expand and contract during operation. - Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
Claims (4)
- A fan case structure comprising:a composite fan case structure (30) having a first coefficient of thermal expansion;a continuous ring-shaped liner (44) having a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion, wherein the second coefficient of thermal expansion is greater than the first coefficient of thermal expansion by at least 10 x 10-6/°F (18 x 10-6/°C) andan elastomeric adhesive (46) operatively connecting the liner (44) to the fan case structure (30), characterised in that the adhesive (46) has a 300% elongation or greater, the adhesive (46) configured to accommodate diametrical change in the liner (44) throughout various operating temperatures.
- The fan case structure according to claim 1, wherein the composite fan case structure (30) includes a structure constructed from resin and at least one of carbon fibers and fiberglass, and the liner (44) is an aluminum alloy.
- The fan case structure according to claim 1 or 2, wherein the adhesive (46) is silicone rubber.
- The fan case structure according to any of claims 1 to 3, wherein a rub strip (36) is supported radially inward from and by the liner (44), and the composite fan case structure (30) includes: a composite septum (42) interconnecting the adhesive (46) to a honeycomb structure (40) that is supported by and radially inward from a composite fan case (32).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/366,416 US20130202424A1 (en) | 2012-02-06 | 2012-02-06 | Conformal liner for gas turbine engine fan section |
EP13151360.8A EP2623724B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
Related Parent Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13151360.8A Division-Into EP2623724B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
EP13151360.8A Division EP2623724B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2775104A1 EP2775104A1 (en) | 2014-09-10 |
EP2775104B1 true EP2775104B1 (en) | 2017-03-29 |
Family
ID=47603315
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13151360.8A Active EP2623724B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
EP14158310.4A Active EP2775104B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP13151360.8A Active EP2623724B1 (en) | 2012-02-06 | 2013-01-15 | Conformal liner for gas turbine engine fan section |
Country Status (2)
Country | Link |
---|---|
US (1) | US20130202424A1 (en) |
EP (2) | EP2623724B1 (en) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2501918B (en) * | 2012-05-11 | 2014-06-18 | Rolls Royce Plc | Casing |
EP2940251B1 (en) | 2014-04-28 | 2019-06-12 | Rolls-Royce Corporation | Fan containment case |
DE102014215693B4 (en) | 2014-08-07 | 2017-11-16 | Technische Universität Dresden | Strain-adapted engine inter-housing in composite construction and modular system for an engine intermediate housing |
US10378554B2 (en) | 2014-09-23 | 2019-08-13 | Pratt & Whitney Canada Corp. | Gas turbine engine with partial inlet vane |
US10145301B2 (en) | 2014-09-23 | 2018-12-04 | Pratt & Whitney Canada Corp. | Gas turbine engine inlet |
US9938848B2 (en) * | 2015-04-23 | 2018-04-10 | Pratt & Whitney Canada Corp. | Rotor assembly with wear member |
US9957807B2 (en) | 2015-04-23 | 2018-05-01 | Pratt & Whitney Canada Corp. | Rotor assembly with scoop |
US20170234160A1 (en) * | 2016-02-11 | 2017-08-17 | General Electric Company | Aircraft engine with an impact panel |
FR3048999B1 (en) * | 2016-03-15 | 2018-03-02 | Safran Aircraft Engines | TURBOREACTOR LOW GAME BETWEEN BLOWER AND BLOWER HOUSING |
US10724540B2 (en) | 2016-12-06 | 2020-07-28 | Pratt & Whitney Canada Corp. | Stator for a gas turbine engine fan |
US10690146B2 (en) | 2017-01-05 | 2020-06-23 | Pratt & Whitney Canada Corp. | Turbofan nacelle assembly with flow disruptor |
US10677260B2 (en) * | 2017-02-21 | 2020-06-09 | General Electric Company | Turbine engine and method of manufacturing |
US10480530B2 (en) | 2017-08-25 | 2019-11-19 | United Technologies Corporation | Fan Containment case for gas turbine engines |
US11939871B1 (en) | 2022-10-28 | 2024-03-26 | Rtx Corporation | Abradable material and design for jet engine applications |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4490092A (en) * | 1981-12-21 | 1984-12-25 | United Technologies Corporation | Containment structure |
US4534698A (en) * | 1983-04-25 | 1985-08-13 | General Electric Company | Blade containment structure |
US5388959A (en) * | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
US6146089A (en) * | 1998-11-23 | 2000-11-14 | General Electric Company | Fan containment structure having contoured shroud for optimized tip clearance |
US6203273B1 (en) * | 1998-12-22 | 2001-03-20 | United Technologies Corporation | Rotary machine |
US6382905B1 (en) * | 2000-04-28 | 2002-05-07 | General Electric Company | Fan casing liner support |
US6732502B2 (en) * | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
FR2859002A1 (en) * | 2003-08-18 | 2005-02-25 | Snecma Moteurs | Abradable surface for gas turbine engine housing surrounding fan, is made from a resin with glass balls over a layer of thermoformable foam |
US9017814B2 (en) * | 2007-10-16 | 2015-04-28 | General Electric Company | Substantially cylindrical composite articles and fan casings |
US8500390B2 (en) * | 2010-05-20 | 2013-08-06 | Pratt & Whitney Canada Corp. | Fan case with rub elements |
-
2012
- 2012-02-06 US US13/366,416 patent/US20130202424A1/en not_active Abandoned
-
2013
- 2013-01-15 EP EP13151360.8A patent/EP2623724B1/en active Active
- 2013-01-15 EP EP14158310.4A patent/EP2775104B1/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
US20130202424A1 (en) | 2013-08-08 |
EP2623724B1 (en) | 2015-05-27 |
EP2623724A1 (en) | 2013-08-07 |
EP2775104A1 (en) | 2014-09-10 |
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