US20130251500A1 - Gas turbine engine case with heating layer and method - Google Patents
Gas turbine engine case with heating layer and method Download PDFInfo
- Publication number
- US20130251500A1 US20130251500A1 US13/428,558 US201213428558A US2013251500A1 US 20130251500 A1 US20130251500 A1 US 20130251500A1 US 201213428558 A US201213428558 A US 201213428558A US 2013251500 A1 US2013251500 A1 US 2013251500A1
- Authority
- US
- United States
- Prior art keywords
- case
- heating layer
- rotor
- 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.)
- Abandoned
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/62—Electrical actuators
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
An assembly of a rotor and case for a gas turbine engine comprises a rotor having a plurality of circumferential blades each with a blade tip. A case comprises a structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and the annular body, and a heating layer connected to the at least one structural layer. The heating layer has a resistivity to heat the structural layer when an electric current passes through the heating layer. An electric power source supplies current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance. A method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine is also provided.
Description
- The application relates generally to gas turbine engines and, more particularly, to a method and means to control the clearance between compressor or turbine blades and the corresponding compressor/engine case.
- Compressor blade tip clearances are conventionally built larger than optimal to avoid blade rub in some flight conditions, such as takeoff and slam acceleration. The clearances are larger than optimal to compensate for a faster blade growth rate relative to the case growth rate because of a faster blade heat ramp rate and blade growth from centrifugal force. Compressor blade growth rate may also be faster than the case growth rate because the blades heat up faster due to their lower thermal mass, larger surface area to volume ratio, thinner wall thickness, and/or exposure to heat from all sides rather than from the gas side only as for the compressor case or engine case.
- In one aspect, there is provided an assembly of a rotor and case for a gas turbine engine comprising: a rotor having a plurality of circumferential blades, each of the blade having a blade tip; a case comprising at least one structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and an inner surface of the annular body, and a heating layer connected to the at least one structural layer, the heating layer having a resistivity to heat the structural layer when an electric current passes through the heating layer; and an electric power source connected to the heating layer and supplying current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance between the rotor and the case.
- In a second aspect, there is provided a method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine, comprising: applying a heating layer on the case; determining that gas turbine engine conditions require an increase in diameter of the case for tip clearance; and supplying electric current to the heating layer on the case to increase the diameter.
- Further details of these and other aspects of the present invention will be apparent from the detailed description and figures included below.
- Reference is now made to the accompanying figures, in which:
-
FIG. 1 is a schematic cross-sectional view of a turbofan gas turbine engine; and -
FIG. 2 is a schematic sectional view of a clearance between a blade and a case, with an electrically-powered heating layer in accordance with the present disclosure. -
FIG. 1 illustrates a turbofangas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication afan 12 through which ambient air is propelled within anengine case 13, amultistage compressor 14 within acompressor case 15 for pressurizing the air, acombustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine section 18 for extracting energy from the combustion gases. - Referring to
FIG. 2 , a blade is shown enlarged at 20. Theblade 20 is one of multiple blades of a rotor, whether it be part of thefan 12 or thecompressor 14, Theblade 20 is illustrated as having ablade tip 21. Theblade tip 21 is shown as having a straight profile. It is understood that theblade tip 21 may have any appropriate profile as alternatives to the straight profile of - A clearance A is defined between the
blade tip 21 and aninner surface 30 of thecase 13/15. Thecase 13/15 is illustrated as consisting of one structural layer (e.g., sheet metal) and has anouter surface 31. However, thecase 13/15 may have additional structural layers, typically radially outward of theouter surface 31. - A heating layer is generally shown at 32 and is against the
outer surface 31. Theheating layer 32 is of the type heating up when an electrical current is passed through it. In accordance with an embodiment, theheating layer 32 is an electric heater coating that is applied (e.g., sprayed, painted, printed, etc.) to theouter surface 31. One suitable type of coating used asheating layer 32 is a product provided by Datec Coating Corporation. In accordance with another embodiment, theheating layer 32 consists of heating foil that is applied against theouter surface 31, In both embodiments, the installation of theheating layer 32 is readily effected when compared to existing prior art system using coils, etc. When heater coating is used, applying the coating may be similar to applying a coat of paint. Moreover, theheating layer 32 may be on either side of thecase 13/15 where possible, of sandwiched between layers of thecase 13/15, etc. In both cases, theheating layer 32 must be made of a material having a minimum resistivity to generate sufficient heat from the electric current circulated therein. - The
heating layer 32 is therefore wired to anelectric power source 40, for instance by way of wires 41 (i.e., leads, lead wires) on opposite sides of thelayer 32. Any appropriate type of arrangements may be used to allow a current supply through theheating layer 32 from theelectric power source 40. It is also considered to have multiple circuits for instance in parallel to heat up theheating layer 32 in segments. - According to the present disclosure, there is provided a smaller cold tip clearance between blade tip and the case then in conventional arrangements, such that the engine as the smallest tip clearance at cruise condition. The case is electrically heated for the case growth rate to better match the blade growth rate, in some flight conditions. For instance, at takeoff or at slam acceleration where blade rub could occur, the case is heated up by circulating current from the
electric power source 40 in theheating layer 32, thereby increasing the case growth rate. The electric heating from theelectric power source 40 may be switched off at cruise condition. In other words, thecase 13/15 is heated up when large tip clearance is needed to avoid rubbing, and the electric heating is switched off when the small clearance is needed for better performance. In an embodiment, theheating layer 32 is sandwiched between different layers of thecase 13/15. - The
electric power source 40 may therefore comprise a controller or like processing unit to determine the flight conditions in which the gas turbine engine is operated. For instance, theelectric power source 40 may have its controller connected to aircraft command center or to an engine control unit to receive this information. Alternatively, theelectric power source 40 may have its controller connected to various probes to determine the flight conditions, such as temperature probes, manometers, etc. Theelectric power source 40 may therefore monitor the flight conditions to calculate an actual tip clearance. Theelectric power source 40 may then actively adjust the size of thecase 13/15 by determining the amount of current required to reach the desired case size, as a function of the known resistivity of theheating layer 32. - The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. For example, multiple heating layers (e.g., of different types) may be provided on the case to increase heating. Various wiring arrangements may be used to supply electric current to the
heating layer 32. Theheating layer 32 may cover a portion or most of thecase 13/15 opposite the rotor. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
Claims (12)
1. An assembly of a rotor and case for a gas turbine engine comprising:
a rotor having a plurality of circumferential blades, each of the blade having a blade tip;
a case comprising at least one structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and an inner surface of the annular body, and a heating layer connected to the at least one structural layer, the heating layer having a resistivity to heat the structural layer when an electric current passes through the heating layer; and
an electric power source connected to the heating layer and supplying current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance between the rotor and the case.
2. The assembly according to claim 1 , wherein the heating layer is a heater coating applied to one of the surfaces of the structural layer.
3. The assembly according to claim 1 , wherein the heating layer is a heating foil applied to one of the surfaces of structural layer.
4. The assembly according to claim 1 , wherein the heating layer is against an outer surface of structural layer.
5. The assembly according to claim 1 , wherein the case is a compressor case and the rotor is a compressor rotor.
6. The assembly according to claim 1 , wherein the case is a turbine case and the rotor is a turbine rotor.
7. A method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine, comprising:
applying a heating layer on the case;
determining that gas turbine engine conditions require an increase in diameter of the case for tip clearance; and
supplying electric current to the heating layer on the case to increase the diameter.
8. The method according to claim 7 , wherein determining that gas turbine engine conditions require an increase in diameter comprises determining that the gas turbine engine is in takeoff or slam acceleration.
9. The method according to claim 7 , further comprising stopping a supply of electric current when gas turbine engine conditions no longer require an increase in diameter of the case.
10. The method according to claim 9 , wherein stopping the supply of electric current occurs during cruise conditions of the gas turbine engine.
11. The method according to claim 7 , wherein applying a heating layer on the case comprises applying a heater coating to one of the surfaces of the case.
12. The method according to claim 7 , wherein applying a heating layer on the case comprises applying a heating foil to one of the surfaces of the case.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/428,558 US20130251500A1 (en) | 2012-03-23 | 2012-03-23 | Gas turbine engine case with heating layer and method |
CA2809802A CA2809802A1 (en) | 2012-03-23 | 2013-03-15 | Gas turbine engine case with heating layer and method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/428,558 US20130251500A1 (en) | 2012-03-23 | 2012-03-23 | Gas turbine engine case with heating layer and method |
Publications (1)
Publication Number | Publication Date |
---|---|
US20130251500A1 true US20130251500A1 (en) | 2013-09-26 |
Family
ID=49211948
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/428,558 Abandoned US20130251500A1 (en) | 2012-03-23 | 2012-03-23 | Gas turbine engine case with heating layer and method |
Country Status (2)
Country | Link |
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US (1) | US20130251500A1 (en) |
CA (1) | CA2809802A1 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140271152A1 (en) * | 2013-03-13 | 2014-09-18 | Jose L. Rodriguez | Turbine engine temperature control system with heating element for a gas turbine engine |
WO2019099009A1 (en) * | 2017-11-16 | 2019-05-23 | Siemens Aktiengesellschaft | Gas turbine clearance control system including embedded electrical heating circuitry |
US20190345835A1 (en) * | 2018-05-14 | 2019-11-14 | United Technologies Corporation | Electric heating for turbomachinery clearance control |
US10760444B2 (en) * | 2018-05-14 | 2020-09-01 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control powered by hybrid energy storage system |
US11187247B1 (en) * | 2021-05-20 | 2021-11-30 | Florida Turbine Technologies, Inc. | Gas turbine engine with active clearance control |
US11319830B2 (en) * | 2019-05-16 | 2022-05-03 | Safran Aircraft Engines | Control of clearance between aircraft rotor blades and a casing |
US11486266B2 (en) | 2019-07-02 | 2022-11-01 | General Electric Company | Turbomachinery heat management system |
US11603773B2 (en) | 2020-04-28 | 2023-03-14 | General Electric Company | Turbomachinery heat transfer system |
Citations (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2004777A (en) * | 1933-05-27 | 1935-06-11 | Gen Electric | Elastic fluid turbine |
US2540472A (en) * | 1949-05-02 | 1951-02-06 | A V Roe Canada Ltd | Electrically heated blade and process of manufacture |
US2547934A (en) * | 1948-06-09 | 1951-04-10 | Peter L Gill | Induction heater for axial flow air compressors |
US2745969A (en) * | 1951-10-25 | 1956-05-15 | Tech Studien Ag | Turbo-machines |
US2971334A (en) * | 1955-01-04 | 1961-02-14 | Solar Aircraft Co | Gas turbine engine adaptable for multi-purpose use |
US3647311A (en) * | 1970-04-23 | 1972-03-07 | Westinghouse Electric Corp | Turbine interstage seal assembly |
US3923415A (en) * | 1974-06-13 | 1975-12-02 | Westinghouse Electric Corp | Steam turbine erosion reduction by ultrasonic energy generation |
US3989966A (en) * | 1973-03-27 | 1976-11-02 | Klein, Schanzlin & Becker Aktiengesellschaft | Apparatus for circulating cooling and lubricating liquids and the like particularly after shutdown of the apparatus |
US3997758A (en) * | 1974-03-14 | 1976-12-14 | Westinghouse Electric Corporation | Moisture control device for steam turbines |
US4334822A (en) * | 1979-06-06 | 1982-06-15 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Circumferential gap seal for axial-flow machines |
US4482293A (en) * | 1981-03-20 | 1984-11-13 | Rolls-Royce Limited | Casing support for a gas turbine engine |
US4584836A (en) * | 1985-01-29 | 1986-04-29 | Westinghouse Electric Corp. | Steam turbine restart temperature maintenance system and method |
US4856272A (en) * | 1988-05-02 | 1989-08-15 | United Technologies Corporation | Method for maintaining blade tip clearance |
US4902139A (en) * | 1988-04-13 | 1990-02-20 | General Electric Company | Apparatus and method for measuring the thermal performance of a heated or cooled component |
US4999991A (en) * | 1989-10-12 | 1991-03-19 | United Technologies Corporation | Synthesized feedback for gas turbine clearance control |
US5228195A (en) * | 1990-09-25 | 1993-07-20 | United Technologies Corporation | Apparatus and method for a stator assembly of a rotary machine |
US5228828A (en) * | 1991-02-15 | 1993-07-20 | General Electric Company | Gas turbine engine clearance control apparatus |
US5344696A (en) * | 1990-01-24 | 1994-09-06 | Hastings Otis | Electrically conductive laminate for temperature control of aircraft surface |
US5504307A (en) * | 1990-07-13 | 1996-04-02 | Ebara Corporation | Heat transfer material for heating and heating unit and heating apparatus using same material |
US5630702A (en) * | 1994-11-26 | 1997-05-20 | Asea Brown Boveri Ag | Arrangement for influencing the radial clearance of the blading in axial-flow compressors including hollow spaces filled with insulating material |
US6145787A (en) * | 1997-05-20 | 2000-11-14 | Thermion Systems International | Device and method for heating and deicing wind energy turbine blades |
US6194692B1 (en) * | 1998-10-02 | 2001-02-27 | Engelhard Corporation | Electric heating sheet and method of making the same |
US6725645B1 (en) * | 2002-10-03 | 2004-04-27 | General Electric Company | Turbofan engine internal anti-ice device |
US20080069683A1 (en) * | 2006-09-15 | 2008-03-20 | Tagir Nigmatulin | Methods and systems for controlling gas turbine clearance |
US20080089775A1 (en) * | 2006-10-13 | 2008-04-17 | General Electric Company | Plasma blade tip clearance control |
US20080156790A1 (en) * | 2006-12-28 | 2008-07-03 | United Technologies Corporation | Electrical connection for titanium metal heater in jet turbine applications |
US7431557B2 (en) * | 2006-05-25 | 2008-10-07 | General Electric Company | Compensating for blade tip clearance deterioration in active clearance control |
US20090037035A1 (en) * | 2007-08-03 | 2009-02-05 | John Erik Hershey | Aircraft gas turbine engine blade tip clearance control |
US7584618B2 (en) * | 2004-06-15 | 2009-09-08 | Snecma | Controlling air flow to a turbine shroud for thermal control |
US20090297330A1 (en) * | 2006-08-09 | 2009-12-03 | Razzell Anthony G | Blade clearance arrangement |
US7722310B2 (en) * | 2004-12-17 | 2010-05-25 | General Electric Company | System and method for measuring clearance between two objects |
US7789620B2 (en) * | 2006-02-16 | 2010-09-07 | United Technologies Corporation | Heater assembly for deicing and/or anti-icing a component |
US20100247283A1 (en) * | 2009-03-25 | 2010-09-30 | General Electric Company | Method and apparatus for clearance control |
US20100284795A1 (en) * | 2007-12-28 | 2010-11-11 | General Electric Company | Plasma Clearance Controlled Compressor |
US20110027068A1 (en) * | 2009-07-28 | 2011-02-03 | General Electric Company | System and method for clearance control in a rotary machine |
US20110167820A1 (en) * | 2010-01-12 | 2011-07-14 | Mikael Fredriksson | Heating system for a turbine |
US20120156007A1 (en) * | 2010-12-16 | 2012-06-21 | Rolls-Royce Plc | Clearance control arrangement |
US8740546B2 (en) * | 2008-04-30 | 2014-06-03 | Siemens Aktiengesellschaft | Guide vane for a condensation steam turbine and associated condensation steam turbine |
US20140314568A1 (en) * | 2011-12-30 | 2014-10-23 | Rolls-Royce North American Technologies,Inc. | Gas turbine engine tip clearance control |
-
2012
- 2012-03-23 US US13/428,558 patent/US20130251500A1/en not_active Abandoned
-
2013
- 2013-03-15 CA CA2809802A patent/CA2809802A1/en not_active Abandoned
Patent Citations (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2004777A (en) * | 1933-05-27 | 1935-06-11 | Gen Electric | Elastic fluid turbine |
US2547934A (en) * | 1948-06-09 | 1951-04-10 | Peter L Gill | Induction heater for axial flow air compressors |
US2540472A (en) * | 1949-05-02 | 1951-02-06 | A V Roe Canada Ltd | Electrically heated blade and process of manufacture |
US2745969A (en) * | 1951-10-25 | 1956-05-15 | Tech Studien Ag | Turbo-machines |
US2971334A (en) * | 1955-01-04 | 1961-02-14 | Solar Aircraft Co | Gas turbine engine adaptable for multi-purpose use |
US3647311A (en) * | 1970-04-23 | 1972-03-07 | Westinghouse Electric Corp | Turbine interstage seal assembly |
US3989966A (en) * | 1973-03-27 | 1976-11-02 | Klein, Schanzlin & Becker Aktiengesellschaft | Apparatus for circulating cooling and lubricating liquids and the like particularly after shutdown of the apparatus |
US3997758A (en) * | 1974-03-14 | 1976-12-14 | Westinghouse Electric Corporation | Moisture control device for steam turbines |
US3923415A (en) * | 1974-06-13 | 1975-12-02 | Westinghouse Electric Corp | Steam turbine erosion reduction by ultrasonic energy generation |
US4334822A (en) * | 1979-06-06 | 1982-06-15 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Circumferential gap seal for axial-flow machines |
US4482293A (en) * | 1981-03-20 | 1984-11-13 | Rolls-Royce Limited | Casing support for a gas turbine engine |
US4584836A (en) * | 1985-01-29 | 1986-04-29 | Westinghouse Electric Corp. | Steam turbine restart temperature maintenance system and method |
US4902139A (en) * | 1988-04-13 | 1990-02-20 | General Electric Company | Apparatus and method for measuring the thermal performance of a heated or cooled component |
US4856272A (en) * | 1988-05-02 | 1989-08-15 | United Technologies Corporation | Method for maintaining blade tip clearance |
US4999991A (en) * | 1989-10-12 | 1991-03-19 | United Technologies Corporation | Synthesized feedback for gas turbine clearance control |
US5344696A (en) * | 1990-01-24 | 1994-09-06 | Hastings Otis | Electrically conductive laminate for temperature control of aircraft surface |
US5504307A (en) * | 1990-07-13 | 1996-04-02 | Ebara Corporation | Heat transfer material for heating and heating unit and heating apparatus using same material |
US5228195A (en) * | 1990-09-25 | 1993-07-20 | United Technologies Corporation | Apparatus and method for a stator assembly of a rotary machine |
US5228828A (en) * | 1991-02-15 | 1993-07-20 | General Electric Company | Gas turbine engine clearance control apparatus |
US5630702A (en) * | 1994-11-26 | 1997-05-20 | Asea Brown Boveri Ag | Arrangement for influencing the radial clearance of the blading in axial-flow compressors including hollow spaces filled with insulating material |
US6145787A (en) * | 1997-05-20 | 2000-11-14 | Thermion Systems International | Device and method for heating and deicing wind energy turbine blades |
US6194692B1 (en) * | 1998-10-02 | 2001-02-27 | Engelhard Corporation | Electric heating sheet and method of making the same |
US6725645B1 (en) * | 2002-10-03 | 2004-04-27 | General Electric Company | Turbofan engine internal anti-ice device |
US7584618B2 (en) * | 2004-06-15 | 2009-09-08 | Snecma | Controlling air flow to a turbine shroud for thermal control |
US7722310B2 (en) * | 2004-12-17 | 2010-05-25 | General Electric Company | System and method for measuring clearance between two objects |
US7789620B2 (en) * | 2006-02-16 | 2010-09-07 | United Technologies Corporation | Heater assembly for deicing and/or anti-icing a component |
US7431557B2 (en) * | 2006-05-25 | 2008-10-07 | General Electric Company | Compensating for blade tip clearance deterioration in active clearance control |
US20090297330A1 (en) * | 2006-08-09 | 2009-12-03 | Razzell Anthony G | Blade clearance arrangement |
US20080069683A1 (en) * | 2006-09-15 | 2008-03-20 | Tagir Nigmatulin | Methods and systems for controlling gas turbine clearance |
US20080089775A1 (en) * | 2006-10-13 | 2008-04-17 | General Electric Company | Plasma blade tip clearance control |
US20080156790A1 (en) * | 2006-12-28 | 2008-07-03 | United Technologies Corporation | Electrical connection for titanium metal heater in jet turbine applications |
US20090037035A1 (en) * | 2007-08-03 | 2009-02-05 | John Erik Hershey | Aircraft gas turbine engine blade tip clearance control |
US20100284795A1 (en) * | 2007-12-28 | 2010-11-11 | General Electric Company | Plasma Clearance Controlled Compressor |
US8740546B2 (en) * | 2008-04-30 | 2014-06-03 | Siemens Aktiengesellschaft | Guide vane for a condensation steam turbine and associated condensation steam turbine |
US20100247283A1 (en) * | 2009-03-25 | 2010-09-30 | General Electric Company | Method and apparatus for clearance control |
US20110027068A1 (en) * | 2009-07-28 | 2011-02-03 | General Electric Company | System and method for clearance control in a rotary machine |
US20110167820A1 (en) * | 2010-01-12 | 2011-07-14 | Mikael Fredriksson | Heating system for a turbine |
US20120156007A1 (en) * | 2010-12-16 | 2012-06-21 | Rolls-Royce Plc | Clearance control arrangement |
US20140314568A1 (en) * | 2011-12-30 | 2014-10-23 | Rolls-Royce North American Technologies,Inc. | Gas turbine engine tip clearance control |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140271152A1 (en) * | 2013-03-13 | 2014-09-18 | Jose L. Rodriguez | Turbine engine temperature control system with heating element for a gas turbine engine |
US9279339B2 (en) * | 2013-03-13 | 2016-03-08 | Siemens Aktiengesellschaft | Turbine engine temperature control system with heating element for a gas turbine engine |
WO2019099009A1 (en) * | 2017-11-16 | 2019-05-23 | Siemens Aktiengesellschaft | Gas turbine clearance control system including embedded electrical heating circuitry |
US20190345835A1 (en) * | 2018-05-14 | 2019-11-14 | United Technologies Corporation | Electric heating for turbomachinery clearance control |
US10760444B2 (en) * | 2018-05-14 | 2020-09-01 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control powered by hybrid energy storage system |
US11111809B2 (en) | 2018-05-14 | 2021-09-07 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control |
US11421545B2 (en) | 2018-05-14 | 2022-08-23 | Raytheon Technologies Corporation | Electric heating for turbomachinery clearance control powered by hybrid energy storage system |
US11319830B2 (en) * | 2019-05-16 | 2022-05-03 | Safran Aircraft Engines | Control of clearance between aircraft rotor blades and a casing |
US11486266B2 (en) | 2019-07-02 | 2022-11-01 | General Electric Company | Turbomachinery heat management system |
US11603773B2 (en) | 2020-04-28 | 2023-03-14 | General Electric Company | Turbomachinery heat transfer system |
US11187247B1 (en) * | 2021-05-20 | 2021-11-30 | Florida Turbine Technologies, Inc. | Gas turbine engine with active clearance control |
US11815106B1 (en) | 2021-05-20 | 2023-11-14 | Florida Turbine Technologies, Inc. | Gas turbine engine with active clearance control |
Also Published As
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