WO2006059976A1 - Turbine engine with a rotor speed sensor and corresponding operating method - Google Patents

Turbine engine with a rotor speed sensor and corresponding operating method Download PDF

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Publication number
WO2006059976A1
WO2006059976A1 PCT/US2004/039978 US2004039978W WO2006059976A1 WO 2006059976 A1 WO2006059976 A1 WO 2006059976A1 US 2004039978 W US2004039978 W US 2004039978W WO 2006059976 A1 WO2006059976 A1 WO 2006059976A1
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WO
WIPO (PCT)
Prior art keywords
blades
fan
turbine
turbine engine
rotor assembly
Prior art date
Application number
PCT/US2004/039978
Other languages
French (fr)
Inventor
James W. Norris
Craig A. Nordeen
Original Assignee
United Technologies Corporation
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corporation filed Critical United Technologies Corporation
Priority to PCT/US2004/039978 priority Critical patent/WO2006059976A1/en
Publication of WO2006059976A1 publication Critical patent/WO2006059976A1/en

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/06—Arrangement of sensing elements responsive to speed
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/068—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type being characterised by a short axial length relative to the diameter
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
    • G01P3/42—Devices characterised by the use of electric or magnetic means
    • G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
    • G01P3/48—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
    • G01P3/42—Devices characterised by the use of electric or magnetic means
    • G01P3/44—Devices characterised by the use of electric or magnetic means for measuring angular speed
    • G01P3/48—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
    • G01P3/481—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
    • G01P3/488—Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by variable reluctance detectors

Definitions

  • the present invention relates to turbine engines, and more particularly to a 5 rotor speed sensor for a turbine engine, such as a tip turbine engine.
  • An aircraft gas turbine engine of the conventional turbofan type generally includes a forward bypass fan, a low pressure compressor, a middle core engine, and an aft low pressure turbine, all located along a common longitudinal axis.
  • a high pressure compressor and a high pressure turbine of the core engine are
  • the high pressure compressor is rotatably driven to compress air entering the core engine to a relatively high pressure. This high pressure air is then mixed with fuel in a combustor, where it is ignited to form a high energy gas stream. The gas stream flows axially aft to rotatably drive the high pressure turbine, which rotatably drives the high pressure compressor via the high
  • the gas stream leaving the high pressure turbine is expanded through the low pressure turbine, which rotatably drives the bypass fan and low pressure compressor via a low spool shaft.
  • Tip turbine engines include hollow fan blades that receive core airflow therethrough
  • the tip turbine engine provides a thrust-to-weight ratio equivalent to or greater than conventional turbofan engines of the same class, but within a package of significantly shorter length.
  • Conventional gas turbine engines include a gearbox driven by the high spool shaft. The rotational speed of the high spool is measured at the gearbox for purposes of controlling the engine.
  • tip turbine engines do not require a gearbox.
  • the conventional method of measuring the speed of the fan rotor is not necessarily applicable.
  • a turbine engine includes at least one sensor mounted adjacent a fan rotor assembly.
  • the sensor measures a rate of rotation of the fan rotor assembly by detecting the temporary proximity, or the passage, of a portion of the fan rotor assembly during rotation.
  • the sensor detects the proximity of at least one of a plurality of fan blades to determine the rate of rotation of the fan rotor assembly.
  • the sensor detects the proximity of at least one of a plurality of turbine blades mounted to the fan rotor assembly. By also measuring the time between consecutive passages of the portion of the fan rotor assembly or the frequency with which the portion of the fan rotor assembly passes the sensor, the rate of rotation is determined.
  • the sensor may be an electromagnetic sensor that detects the proximity of ferromagnetic portions of the fan rotor assembly, such as the fan blades or the turbine blades. Other types of sensors could also be utilized. Alternative locations for the sensor are also disclosed.
  • Figure 1 is a partial sectional perspective view of a tip turbine engine; and Figure 2 is a longitudinal sectional view of the tip turbine engine of Figure 1 along an engine centerline.
  • FIG. 1 illustrates a general perspective partial sectional view of a tip turbine engine (TTE) type gas turbine engine 10.
  • the engine 10 includes an outer nacelle 12, a rotationally fixed static outer support structure 14 and a rotationally fixed static inner support structure 16.
  • a plurality of fan inlet guide vanes 18 are mounted between the static outer support structure 14 and the static inner support structure 16.
  • Each inlet guide vane preferably includes a variable trailing edge 18 A.
  • a nosecone 20 is preferably located along the engine centerline or axis A to improve airflow into an axial compressor 22, which is mounted about the engine centerline A behind the nosecone 20.
  • a fan-turbine rotor assembly 24 is mounted for rotation about the engine centerline A aft of the axial compressor 22.
  • the fan-turbine rotor assembly 24 includes a plurality of hollow fan blades 28 to provide internal, centrifugal compression of the compressed airflow from the axial compressor 22 for distribution to an annular combustor 30 located within the rotationally fixed static outer support structure 14.
  • a turbine 32 includes a plurality of tip turbine blades 34 (two stages shown) which rotatably drive the hollow fan blades 28 relative to a plurality of tip turbine stators 36 which extend radially inwardly from the rotationally fixed static outer support structure 14.
  • the annular combustor 30 is disposed axially forward of the turbine 32 and communicates with the turbine 32.
  • the rotationally fixed static inner support structure 16 includes a splitter 40, a static inner support housing 42 and a static outer support housing 44 located coaxial with said engine centerline A.
  • the axial compressor 22 includes the axial compressor rotor 46, from which a plurality of compressor blades 52 extend radially outwardly, and a fixed compressor case 50.
  • a plurality of compressor vanes 54 extend radially inwardly from the compressor case 50 between stages of the compressor blades 52.
  • the compressor blades 52 and compressor vanes 54 are arranged circumferentially about the axial compressor rotor 46 in stages (three stages of compressor blades 52 and three stages of compressor vanes 54 are shown in this example).
  • the axial compressor rotor 46 is mounted for rotation upon the static inner support housing 42 through a forward bearing assembly 68 and an aft bearing assembly 62.
  • the fan-turbine rotor assembly 24 includes a fan hub 64 that supports a plurality of the hollow fan blades 28.
  • Each fan blade 28 includes an inducer section 66, a hollow fan blade section 72 and a diffuser section 74.
  • the inducer section 66 receives airflow from the axial compressor 22 generally parallel to the engine centerline A and turns the airflow from an axial airflow direction toward a radial airflow direction.
  • the airflow is radially communicated through a core airflow passage 80 within the fan blade section 72 where the airflow is centrifugally compressed. From the core airflow passage 80, the airflow is diffused and turned once again toward an axial airflow direction toward the annular combustor 30.
  • the airflow is diffused axially forward in the engine 10, however, the airflow may alternatively be communicated in another direction.
  • a rate sensor 82 is mounted adjacent the fan-turbine rotor assembly 24.
  • the rate sensor 82 may be an electromagnetic proximity sensor, which detects the proximity of a ferromagnetic portion of the fan-turbine rotor assembly 24 as it passes the rate sensor 82 upon each rotation. By measuring the elapsed time between pulses (or the frequency of the pulses) generated by proximity of the ferromagnetic portions of the fan-turbine rotor assembly 24, the rate of rotation of the fan-turbine rotor assembly 24 is determined. This calculated rate, or the raw pulse data, may be sent to a data processor 84 or CPU, which controls the engine 10 based upon the rate of rotation of the fan-turbine rotor assembly 24.
  • the ferromagnetic portions are the hollow fan blades 28 and the rate sensor 82 is mounted adjacent the hollow fan blades 28 as shown.
  • the turbine blades 34 may comprise the ferromagnetic portions, as indicated by the optional location of the rate sensor 82a, shown in phantom.
  • the inducers 66 may comprise the ferromagnetic portions, as indicated by the optional locations of the rate sensors 82b or 82c, also shown in phantom.
  • the rate sensor 82 alternatively utilizes optical, acoustic or other known techniques for detecting presence, speed and/or motion.
  • the tip turbine engine 10 does not necessarily include a gearbox.
  • the tip turbine engine 10 may optionally include a gearbox assembly 90 aft of the fan-turbine rotor assembly 24, such that the fan-turbine rotor assembly 24 rotatably drives the axial compressor 22 via the gearbox assembly 90.
  • the gearbox assembly 90 provides a speed increase at a 3.34-to-one ratio.
  • the gearbox assembly 90 may be an epicyclic gearbox, such as a planetary gearbox as shown, that is mounted for rotation between the static inner support housing 42 and the static outer support housing 44.
  • the gearbox assembly 90 includes a sun gear 92, which rotates the axial compressor 22, and a planet carrier 94, which rotates with the fan-turbine rotor assembly 24.
  • a plurality of first planet gears 93 each engage the sun gear 92 and a rotationally fixed ring gear 95.
  • the first planet gears 93 are mounted to the planet carrier 94.
  • the gearbox assembly 90 is mounted for rotation between the sun gear 92 and the static outer support housing 44 through a gearbox forward bearing 96 and a gearbox rear bearing 98.
  • the gearbox assembly 90 may alternatively, or additionally, reverse the direction of rotation and/or may provide a decrease in rotation speed. In operation, core airflow enters the axial compressor 22, where it is compressed by the compressor blades 52.
  • the compressed air from the axial compressor 22 enters the inducer section 66 in a direction generally parallel to the engine centerline A, and is then turned by the inducer section 66 radially outwardly through the core airflow passage 80 of the hollow fan blades 28.
  • the airflow is further compressed centrifugally in the hollow fan blades 28 by rotation of the hollow fan blades 28.
  • From the core airflow passage 80 the airflow is turned and diffused axially forward in the engine 10 into the annular combustor 30.
  • the compressed core airflow from the hollow fan blades 28 is mixed with fuel in the annular combustor 30 and ignited to form a high-energy gas stream.
  • the high-energy gas stream is expanded over the plurality of tip turbine blades 34 mounted about the outer periphery of the fan-turbine rotor assembly 24 to drive the fan-turbine rotor assembly 24, which in turn rotatably drives the axial compressor 22 either directly or via the optional gearbox assembly 90.
  • the fan- turbine rotor assembly 24 discharges fan bypass air axially aft to merge with the core airflow from the turbine 32 in an exhaust case 106.
  • the rate sensor 82 detects the passage of each ferromagnetic portion upon rotation of the fan rotor assembly 24.
  • the rotation rate of the fan rotor assembly 24 is calculated based upon the frequency of the passage of the ferromagnetic portions and used in the data processor 84 as feedback for controlling the tip turbine engine 10.
  • a plurality of exit guide vanes 108 are located between the static outer support housing 44 and the rotationally fixed static outer support structure 14 to guide the combined airflow out of the engine 10 and provide forward thrust.
  • An exhaust mixer 110 mixes the airflow from the turbine blades 34 with the bypass airflow through the fan blades 28.

Abstract

A turbine engine includes at least one rate sensor mounted adjacent a fan rotor assembly. The sensor measures a rate of rotation of the fan rotor assembly by detecting the temporary proximity of a portion of the fan rotor assembly during rotation. In one embodiment, the sensor detects the proximity of at least one of a plurality of fan blades to determine the rate of rotation of the fan rotor assembly. In another embodiment, the sensor detects the proximity of at least one of a plurality of turbine blades mounted to the fan rotor assembly. The sensor may be an electromagnetic sensor that detects the proximity of ferromagnetic portions of the fan rotor assembly, such as the fan blades or the turbine blades.

Description

TURBINE ENGINE WITH A ROTOR SPEED SENSOR AND CORRESPONDING OPERATING METHOD
The present invention relates to turbine engines, and more particularly to a 5 rotor speed sensor for a turbine engine, such as a tip turbine engine.
An aircraft gas turbine engine of the conventional turbofan type generally includes a forward bypass fan, a low pressure compressor, a middle core engine, and an aft low pressure turbine, all located along a common longitudinal axis. A high pressure compressor and a high pressure turbine of the core engine are
10 interconnected by a high spool shaft. The high pressure compressor is rotatably driven to compress air entering the core engine to a relatively high pressure. This high pressure air is then mixed with fuel in a combustor, where it is ignited to form a high energy gas stream. The gas stream flows axially aft to rotatably drive the high pressure turbine, which rotatably drives the high pressure compressor via the high
15 spool shaft. The gas stream leaving the high pressure turbine is expanded through the low pressure turbine, which rotatably drives the bypass fan and low pressure compressor via a low spool shaft.
Although highly efficient, conventional turbofan engines operate in an axial flow relationship. The axial flow relationship results in a relatively complicated
20 elongated engine structure of considerable length relative to the engine diameter. This elongated shape may complicate or prevent packaging of the engine into particular applications.
A recent development in gas turbine engines is the tip turbine engine. Tip turbine engines include hollow fan blades that receive core airflow therethrough
25 such that the interior of the hollow fan blades operate as a centrifugal compressor. Compressed core airflow from the hollow fan blades is mixed with fuel in an annular combustor, where it is ignited to form a high energy gas stream which drives the turbine that is integrated onto the tips of the hollow bypass fan blades for rotation therewith as generally disclosed in U.S. Patent Application Publication
30 Nos.: 20030192303; 20030192304; and 20040025490. The tip turbine engine provides a thrust-to-weight ratio equivalent to or greater than conventional turbofan engines of the same class, but within a package of significantly shorter length. Conventional gas turbine engines include a gearbox driven by the high spool shaft. The rotational speed of the high spool is measured at the gearbox for purposes of controlling the engine. However, tip turbine engines do not require a gearbox.
Therefore, the conventional method of measuring the speed of the fan rotor is not necessarily applicable.
SUMMARY OF THE INVENTION
A turbine engine according to the present invention includes at least one sensor mounted adjacent a fan rotor assembly. The sensor measures a rate of rotation of the fan rotor assembly by detecting the temporary proximity, or the passage, of a portion of the fan rotor assembly during rotation. In one embodiment, the sensor detects the proximity of at least one of a plurality of fan blades to determine the rate of rotation of the fan rotor assembly. In another embodiment, the sensor detects the proximity of at least one of a plurality of turbine blades mounted to the fan rotor assembly. By also measuring the time between consecutive passages of the portion of the fan rotor assembly or the frequency with which the portion of the fan rotor assembly passes the sensor, the rate of rotation is determined.
The sensor may be an electromagnetic sensor that detects the proximity of ferromagnetic portions of the fan rotor assembly, such as the fan blades or the turbine blades. Other types of sensors could also be utilized. Alternative locations for the sensor are also disclosed.
BRIEF DESCRIPTION OF THE DRAWINGS
Other advantages of the present invention can be understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
Figure 1 is a partial sectional perspective view of a tip turbine engine; and Figure 2 is a longitudinal sectional view of the tip turbine engine of Figure 1 along an engine centerline. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
Figure 1 illustrates a general perspective partial sectional view of a tip turbine engine (TTE) type gas turbine engine 10. The engine 10 includes an outer nacelle 12, a rotationally fixed static outer support structure 14 and a rotationally fixed static inner support structure 16. A plurality of fan inlet guide vanes 18 are mounted between the static outer support structure 14 and the static inner support structure 16. Each inlet guide vane preferably includes a variable trailing edge 18 A.
A nosecone 20 is preferably located along the engine centerline or axis A to improve airflow into an axial compressor 22, which is mounted about the engine centerline A behind the nosecone 20.
A fan-turbine rotor assembly 24 is mounted for rotation about the engine centerline A aft of the axial compressor 22. The fan-turbine rotor assembly 24 includes a plurality of hollow fan blades 28 to provide internal, centrifugal compression of the compressed airflow from the axial compressor 22 for distribution to an annular combustor 30 located within the rotationally fixed static outer support structure 14.
A turbine 32 includes a plurality of tip turbine blades 34 (two stages shown) which rotatably drive the hollow fan blades 28 relative to a plurality of tip turbine stators 36 which extend radially inwardly from the rotationally fixed static outer support structure 14. The annular combustor 30 is disposed axially forward of the turbine 32 and communicates with the turbine 32.
Referring to Figure 2, the rotationally fixed static inner support structure 16 includes a splitter 40, a static inner support housing 42 and a static outer support housing 44 located coaxial with said engine centerline A. The axial compressor 22 includes the axial compressor rotor 46, from which a plurality of compressor blades 52 extend radially outwardly, and a fixed compressor case 50. A plurality of compressor vanes 54 extend radially inwardly from the compressor case 50 between stages of the compressor blades 52. The compressor blades 52 and compressor vanes 54 are arranged circumferentially about the axial compressor rotor 46 in stages (three stages of compressor blades 52 and three stages of compressor vanes 54 are shown in this example). The axial compressor rotor 46 is mounted for rotation upon the static inner support housing 42 through a forward bearing assembly 68 and an aft bearing assembly 62.
The fan-turbine rotor assembly 24 includes a fan hub 64 that supports a plurality of the hollow fan blades 28. Each fan blade 28 includes an inducer section 66, a hollow fan blade section 72 and a diffuser section 74. The inducer section 66 receives airflow from the axial compressor 22 generally parallel to the engine centerline A and turns the airflow from an axial airflow direction toward a radial airflow direction. The airflow is radially communicated through a core airflow passage 80 within the fan blade section 72 where the airflow is centrifugally compressed. From the core airflow passage 80, the airflow is diffused and turned once again toward an axial airflow direction toward the annular combustor 30. Preferably, the airflow is diffused axially forward in the engine 10, however, the airflow may alternatively be communicated in another direction.
A rate sensor 82 is mounted adjacent the fan-turbine rotor assembly 24. The rate sensor 82 may be an electromagnetic proximity sensor, which detects the proximity of a ferromagnetic portion of the fan-turbine rotor assembly 24 as it passes the rate sensor 82 upon each rotation. By measuring the elapsed time between pulses (or the frequency of the pulses) generated by proximity of the ferromagnetic portions of the fan-turbine rotor assembly 24, the rate of rotation of the fan-turbine rotor assembly 24 is determined. This calculated rate, or the raw pulse data, may be sent to a data processor 84 or CPU, which controls the engine 10 based upon the rate of rotation of the fan-turbine rotor assembly 24. In the embodiment shown, the ferromagnetic portions are the hollow fan blades 28 and the rate sensor 82 is mounted adjacent the hollow fan blades 28 as shown. Alternatively, the turbine blades 34 may comprise the ferromagnetic portions, as indicated by the optional location of the rate sensor 82a, shown in phantom. As another alternative, the inducers 66 may comprise the ferromagnetic portions, as indicated by the optional locations of the rate sensors 82b or 82c, also shown in phantom. The rate sensor 82 alternatively utilizes optical, acoustic or other known techniques for detecting presence, speed and/or motion.
As indicated above, the tip turbine engine 10 does not necessarily include a gearbox. However, the tip turbine engine 10 may optionally include a gearbox assembly 90 aft of the fan-turbine rotor assembly 24, such that the fan-turbine rotor assembly 24 rotatably drives the axial compressor 22 via the gearbox assembly 90. In the embodiment shown, the gearbox assembly 90 provides a speed increase at a 3.34-to-one ratio. The gearbox assembly 90 may be an epicyclic gearbox, such as a planetary gearbox as shown, that is mounted for rotation between the static inner support housing 42 and the static outer support housing 44. The gearbox assembly 90 includes a sun gear 92, which rotates the axial compressor 22, and a planet carrier 94, which rotates with the fan-turbine rotor assembly 24. A plurality of first planet gears 93 each engage the sun gear 92 and a rotationally fixed ring gear 95. The first planet gears 93 are mounted to the planet carrier 94. The gearbox assembly 90 is mounted for rotation between the sun gear 92 and the static outer support housing 44 through a gearbox forward bearing 96 and a gearbox rear bearing 98. The gearbox assembly 90 may alternatively, or additionally, reverse the direction of rotation and/or may provide a decrease in rotation speed. In operation, core airflow enters the axial compressor 22, where it is compressed by the compressor blades 52. The compressed air from the axial compressor 22 enters the inducer section 66 in a direction generally parallel to the engine centerline A, and is then turned by the inducer section 66 radially outwardly through the core airflow passage 80 of the hollow fan blades 28. The airflow is further compressed centrifugally in the hollow fan blades 28 by rotation of the hollow fan blades 28. From the core airflow passage 80, the airflow is turned and diffused axially forward in the engine 10 into the annular combustor 30. The compressed core airflow from the hollow fan blades 28 is mixed with fuel in the annular combustor 30 and ignited to form a high-energy gas stream. The high-energy gas stream is expanded over the plurality of tip turbine blades 34 mounted about the outer periphery of the fan-turbine rotor assembly 24 to drive the fan-turbine rotor assembly 24, which in turn rotatably drives the axial compressor 22 either directly or via the optional gearbox assembly 90. The fan- turbine rotor assembly 24 discharges fan bypass air axially aft to merge with the core airflow from the turbine 32 in an exhaust case 106. The rate sensor 82 detects the passage of each ferromagnetic portion upon rotation of the fan rotor assembly 24. The rotation rate of the fan rotor assembly 24 is calculated based upon the frequency of the passage of the ferromagnetic portions and used in the data processor 84 as feedback for controlling the tip turbine engine 10.
A plurality of exit guide vanes 108 are located between the static outer support housing 44 and the rotationally fixed static outer support structure 14 to guide the combined airflow out of the engine 10 and provide forward thrust. An exhaust mixer 110 mixes the airflow from the turbine blades 34 with the bypass airflow through the fan blades 28. hi accordance with the provisions of the patent statutes and jurisprudence, exemplary configurations described above are considered to represent a preferred embodiment of the invention. However, it should be noted that the invention can be practiced otherwise than as specifically illustrated and described without departing from its spirit or scope.

Claims

1. A turbine engine comprising: a plurality of blades rotatable about an axis of the turbine engine; and at least one sensor mounted adjacent the plurality of blades, the sensor measuring a rate of rotation of the plurality of blades.
2. The turbine engine of claim 1 wherein the sensor detects a proximity of each of the plurality of fan blades in order to measure the rate of rotation of the plurality of blades.
3. The turbine engine of claim 2 wherein the plurality of blades are a plurality of fan blades extending radially from a fan rotor.
4. The turbine engine of claim 2 wherein the plurality of blades are a plurality of turbine blades.
5. The turbine engine of claim 4 wherein the plurality of turbine blades are radially outward of at least a portion of a plurality of fan blades.
6. The turbine engine of claim 5 wherein the plurality of turbine blades are operatively connected to outer ends of the plurality of fan blades.
7. The turbine engine of claim 6 wherein the sensor is an electromagnetic sensor.
8. The turbine engine of claim 1 wherein the sensor is an electromagnetic sensor.
9. The turbine engine of claim 1 wherein the sensor generates a plurality of pulses at a rate proportional to the rate of rotation of the fan blades.
10. A turbine engine comprising: a fan rotor assembly rotatable about an axis, the fan rotor assembly including a plurality of fan blades; and at least one sensor mounted adjacent the fan rotor assembly, the sensor measuring a rate of rotation of the fan rotor assembly.
11. The turbine engine of claim 10 wherein the sensor detects proximity of at least one of the plurality of fan blades in order to measure the rate of rotation.
12. The turbine engine of claim 10 further including a plurality of turbine blades radially outward of the plurality of fan blades, the plurality of turbine blades being operatively connected to outer ends of the plurality of fan blades.
13. The turbine engine of claim 12 wherein the sensor detects a passage of at least one of the plurality of turbine blades upon each rotation of the fan rotor assembly.
14. The turbine engine of claim 10 wherein the sensor is an electromagnetic sensor.
15. The turbine engine of claim 10 wherein at least one fan blade of the plurality of fan blades defines a compressor chamber extending radially therein.
16. The turbine engine of claim 15 further including at least one combustor receiving core airflow from the compressor chamber, a turbine mounted aft of the at least
17. A method of operating a turbine engine including the steps of: rotatably driving a fan rotor assembly having a plurality of fan blades; and detecting a proximity of portions of the fan rotor assembly to determine a rate of rotation of the fan rotor assembly.
18. The method of claim 17 further including the step of centrifugally compressing core airflow in the interiors of the plurality of fan blades.
19. The method of claim 17 wherein the portions of the fan rotor assembly are the plurality of fan blades.
20. The method of claim 17 wherein the fan rotor assembly is a fan-turbine rotor assembly including a turbine at outward locations on the plurality of fan blades, the turbine including a plurality of turbine blades, wherein the portions are the plurality of turbine blades.
21. The method of claim 17 wherein said step b) is performed by electromagnetically detecting the proximity of the portions of the fan rotor assembly.
22. The method of claim 17 further including the step of generating a plurality of pulses at a rate proportional to the rate of rotation of the fan rotor assembly.
PCT/US2004/039978 2004-12-01 2004-12-01 Turbine engine with a rotor speed sensor and corresponding operating method WO2006059976A1 (en)

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US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
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

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US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
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
ITBO20090734A1 (en) * 2009-11-10 2011-05-11 Alfredo Coccagna CONTROL AND MEASUREMENT GROUP, PARTICULARLY FOR ELECTRIC MOTORS.
EP2325653A1 (en) * 2009-11-17 2011-05-25 Rolls-Royce Deutschland Ltd & Co KG Gas turbine engine with an arrangement for measuring the shaft rotation speed
WO2011152914A2 (en) 2010-03-15 2011-12-08 Rolls-Royce Corporation Determining fan parameters through pressure monitoring
EP2547893A4 (en) * 2010-03-15 2018-01-03 Rolls-Royce Corporation Determining fan parameters through pressure monitoring

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