GB2123568A - Measuring torque on gas- turbine engine shafts - Google Patents
Measuring torque on gas- turbine engine shafts Download PDFInfo
- Publication number
- GB2123568A GB2123568A GB08219698A GB8219698A GB2123568A GB 2123568 A GB2123568 A GB 2123568A GB 08219698 A GB08219698 A GB 08219698A GB 8219698 A GB8219698 A GB 8219698A GB 2123568 A GB2123568 A GB 2123568A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- turbine engine
- gas turbine
- fluid
- shafts
- 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- Withdrawn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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L3/00—Measuring torque, work, mechanical power, or mechanical efficiency, in general
- G01L3/02—Rotary-transmission dynamometers
- G01L3/04—Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Turbines (AREA)
Abstract
A means to detect when relative angular displacement between a first shaft (38) and a second shaft (36) of a gas-turbine engine reaches a predetermined value comprises a number of circumferentially arranged equi-spaced apertures (50 and 46) in the shafts. Each aperture (50) in the first shaft (38) is initially positioned a predetermined angle from the corresponding aperture (46) in the second shaft (36) and a fluid is supplied to the first shaft (38). In operation when torque on the shaft (36) causes the angular displacement between the shafts (36, 38) to reach the predetermined value, the apertures (46, 50) align with each other and the fluid in the first shaft (38) flows out of the shaft (36) through the apertures (46, 50). The fluid supply means has a restrictor and a sensing means to sense a change in pressure difference between the pressure of the fluid on either side of the restrictor. The sensing means may be used to operate a fuel shut-off system. <IMAGE>
Description
SPECIFICATION
Improvements in or relating to gas turbine engines
The present invention relates to gas turbine engines, and in particular it relates to means for detecting when the torque applied to a torque carrying shaft reaches a predetermined value. It is also concerned with a means to shut off a supply of fuel to the gas turbine engine when the torque applied to the torque carrying shaft reaches the predetermined value.
Gas turbine engines comprise one or more torque carrying shaft which drivingly connect a fan or a compressor rotor to one or more corresponding driving turbine rotor/rotors. These torque carrying shafts may be rotating at speeds in excess of 11,000 RPM, and should one of these shafts fail the corresponding turbine will accelerate rapidly due to the removal of the load being driven. If the acceleration of the unloaded turbine is not prevented, the turbine will overspeed and the turbine may burst and cause serious damage to the gas turbine engine.
The present invention seeks to provide means to detect when the torque applied to a shaft reaches a predetermined value.
The invention also seeks to provide means to shut off a supply of fuel to the gas turbine engine when the torque applied to the shaft reaches the predetermined value.
Accordingly the present invention provides a gas turbine engine which comprises a first shaft positioned coaxially within a second shaft, one of the shafts drivingly connects a first rotating assembly to a second rotating assembly, a portion of the first shaft having an outer diameter substantially the same as an inner diameter of the second shaft, a fluid supply to supply fluid to the first shaft, means to detect when a relative angular displacement between the shaft reaches a predetermined value when the gas turbine engine is in operation, said means comprises at least one aperture in the said portion of the first shaft and a corresponding aperture in the second shaft, the aperatures in the first and second shaft lying in the same plane, the aperture in the first shaft being positioned a predetermined angle in the direction of rotation of the shafts from the aperture in the second shaft, in operation when the relative angular displacement between the first and second shafts reaches the predetermined value the apertures in the first and second shafts aligning with each other permitting said fluid to flow out of the first shaft.
The said portion of the first shaft may have a plurality of equi-spaced apertures and the second shaft may have an equal number of equi-spaced apertures, in operation when the relative angular displacement between the first and second shafts reaches the pre-determined value the apertures in the first and second shafts aligning with each other permitting said fluid to flow out of the first shaft.
In a preferred embodiment the second shaft drivingly connects the first rotating assembly to the second rotating assembly, the first shaft extending the full length of the second shaft and the first shaft being secured to the upstream end of the second shaft, the said portion of the first shaft and the apertures in the first and second shaft being positioned at the downstream end of the first and second shafts respectively, in operation the twisting of the second shaft causes the downstream end of the second shaft to be angularly displaced relative to the downstream end of the first shaft.
The fluid supply means may comprise a restrictor, and means to sense a change in pressure difference between the pressure of the fluid on either side of the restrictor when the apertures in the first and second shafts are in alignment with each other permitting fluid to flow out of the first shaft.
The sensing means may comprise a piston which is positioned within, and forms a first and a second chamber with, a cylinder, the first chambe receiving fluid from the fluid supply means from a position on one side of the restrictor and the second chamber receiving fluid from the fluid supply means from a position on the other side of the restrictor, the piston moving in the cylinder when there is a change in pressure difference between the pressure of the fluid on either side of the restrictor.
The sensing means may supply an operating signal to an operating means which causes a supply of fuel to the gas turbine engine to be at least reduced when the sensing means senses a change in pressure difference between the pressure of the fluid on either side of the restrictor.
The piston may have an arm which moves with the piston when there is a change in pressure difference between the pressure of the fluid on either side of the restrictor, the movement of the arm transmitting said operating signal.
The operating means may cause the supply of fuel to the gas turbine engine to be terminated, and the operating means may be a fuel servo system.
The fluid may be oil, and a portion of the fluid supplied to the first shaft may flow through the first shaft and be used to lubricate at least one bearing of the first or second shafts.
The invention will be more fully described by way of example only, with reference to the accompanying drawings in which:
Figure 1 is a cut-away view of a gas turbine engine showing the rotating assemblies, the shafts and the means to detect when a relative angular displacement between the shafts reaches a predetermined value when the gas turbine engine is in operation.
Figure 2 is an enlarged view of the low pressure shaft and a shaft positioned coaxially within the low pressure shaft and the detecting means as shown in figure 1.
Figure 3 is a cross-section along the line A-A in figure 2.
Figure 4 is a diagrammatic view of an oil supply system and a means to sense a change in the pressure of the oil supplied to the shaft positioned coaxially within the low pressure shaft.
Figure 5 is a diagrammatic view of an alternative oil supply system and means to sense a change in the pressure of the oil supplied to the shaft positioned coaxially within the low pressure shaft.
A gas turbine engine 10 as shown in figure 1 comprises in flow series a fan 12 and a core engine 1 6. The core engine 1 6 comprises in flow series an intermediate pressure compressor 18, a high pressure compressor 20, an annular combustion chamber 22, a high pressure turbine 24, an intermediate pressure turbine 26, a low pressure turbine 28 and an exhaust nozzle 30. An annular bypass duct 14 is formed around the core engine 16, and the fan 12, the intermediate and high pressure compressors 1 8 and 20 respectively are connected to the low, intermediate and high pressure turbines 28, 26 and 24 respectively via the low, intermediate and high pressure shafts 36, 34 and 32 respectively.A shaft 38 is positioned coaxially within and is secured to the upstream end of the low pressure shaft 36 and extends the full length of the low pressure shaft 36, but the downstream end of the shaft 38 is not secured to the downstream end of the low pressure shaft 36.
A detection means 40 to detect when a relative angular displacement between the shafts 36 and 38 reaches a predetermined amount when the gas turbine engine is in operation is positioned at the downstream end of the shafts 36 and 38.
In operation air is drawn into the gas turbine engine 10 and is given an initial compression by the fan 12, and the airflow is then divided. A first portion of the air flows through the annular bypass duct 14 around the core engine 16, and a second portion of the air flows into the core engine 1 6.
The second portion of air is further compressed by the intermediate and high pressure compressors 1 8 and 20 respectively before it enters the annular combustion chamber 22. Fuel is injected into the annular combustion chamber 22 and is ignited and burnt in the air to produce hot gases which flow out of the annular combustion chamber 22.
The hot gases drive the high, intermediate and low pressure turbines 24, 26 and 28 respectively before leaving the gas turbine engine 10 through the exhaust nozzle 30. The high, intermediate and low pressure turbines 24, 26 and 28 respectively in turn drive the high and intermediate pressure compressors 20 and 18 and the fan 12 respectively via the shafts 32, 34 and 36 respectively.
As previously mentioned, the shafts may be rotating at speeds in excess of 11000 RPM when the gas turbine engine is in operation. If one of the shafts failed the corresponding turbine rotor or rotors would accelerate rapidly due to the removal of the load it is driving. If the acceleration of the unloaded turbine rotor or rotors is not prevented, the turbine rotor or rotors will overspeed, and the turbine rotor may burst and cause serious damage to the gas turbine engine.
Each turbine rotor is driven by the hot gases
passing through the turbine, and each turbine
rotor drives the corresponding shaft which in turn
drives the corresponding compressor rotor. The
shaft has a degree of twist between its upstream
and downstream ends due to the torque applied to
the shaft. If the shaft is weakened structurally the
twisting of the shaft will increase. If the shaft fails
the turbine rotor becomes unloaded and this leads
to overspeeding of the turbine rotor.
In order to prevent overspeeding of the turbine
rotor, in the present invention any excessive
twisting of the shaft is detected and the supply of
fuel to the gas turbine engine can be cut off.
Figures 2 and 3 show enlarged views of the
detection means 40 and the downstream ends of
the shafts 36 and 38.
The shaft 36 has an annular flange 42 at its
downstream end which extends radially inwards
towards the shaft 38. The annular flange 42 has
an L-shaped cross-section, and a limb 44 of the
annular flange 42 has an inner diameter
substantially the same as the outer diameter of a
portion 48 of the shaft 38. The limb 44 of the
annular flange 42 and the portion 48 of the shaft 38 have a number of circumferentially arranged equi-spaced apertures 46 and 50 respectively.
The apertures 46 and 50 in the limb 44 and the portion 48 of the shaft 38 iie in the same plane, and each aperture 50 in the portion 48 of the shaft 38 is positioned a predetermined angle in the direction of rotation of the shafts 36 and 38 from a corresponding aperture 46 in the limb 44 of the flange 42. A tube 52 fits coaxially within the downstream end of the shaft 38 in order to supply a fluid from a fluid supply to the shaft 38.
To detect twisting of the shaft 36 the shaft 38 is secured coaxially within and to the upstream end of the shaft 36, and the shaft 38 extends the full length of the shaft 36. As the rotational speed of the shaft 36 increases in operation, there is a twisting of the downstream end of the shaft 36 in its direction of rotation with respect to its upstream end. The twisting of the shaft 36 is due to the torque applied to it, and this twisting results in an angular displacement between the downstream end of the shaft 36 and the downstream end of the shaft 38.
In operation, the fluid, in this case oil, supplied to the shaft 38 from the tube 52 may flow the full length of the shaft 38 and be used to lubricate bearings at the upstream end of the shaft 36. Also due to the twisting of the shaft 36, the apertures 46 in the limb 44 of the annular flange 42 are displaced relative to the apertures 50 in the portion 48 of the shaft 38. The angle through which the downstream end of the shaft 36, annular flange 42, limb 44 and apertures 46 are displaced is dependent upon the torque applied to the shaft 36, but the predetermined angle has been chosen to be greater than the angular displacement of the downstream end of the shaft from the pipe 80 to a chamber 98 formed on the other side of the piston 94.An arm 100
However, if for some reason, the angular displacement of the downstream end of the shaft 36 and the associated annular flange 42 with respect to the shaft 38 is greater than under normal operating conditions, the apertures 46 in the limb 44 of the annular flange 42 are displaced angularly until they are in alignment with the apertures 50 in the portion 48 of the shaft 38. The oil in the shaft 38 then flows through the apertures 50 and 46 in the portion 48 of the shaft 38 and the limb 44 of the annular flange 42 to the downstream bearing housing (not shown).
Figure 4 shows a sensing means 54 and part of an oil supply system. Oil from an oil supply is supplied through pipe 56 which has a restrictor 58 to the tube 52 and the shaft 38. A pipe 60 leads from the pipe 56 on one side of the restrictor 58, to a chamber 68 formed on one side of a piston 66 positioned within a cylinder 64, and a pipe 62 leads from the pipe 56 on the other side of the restrictor 58, to a chamber 70 formed on the other side of the piston 66. An arm 72 which extends through the wall of the cylinder 64 from the piston 66 is connected to a fuel shut off system.
In normal operation oil flows from the oil supply through pipe 56 and the restrictor 58 to the tube 52 and the shaft 38. As previously mentioned a portion of the oil flows down the shaft 38 to the bearings (not shown) at the upstream end of the low pressure shaft 36. A portion of the oil flowing through the pipe 56 flows through pipe 60 into the chamber 68 in the cylinder 64, and another portion of oil flows through pipe 62 into the chamber 70.
The piston 66 in the cylinder 64 reaches an equilibrium position as shown in figure 4 as the pressure of the oil in the chambers 68 and 70 is equal.
But, should the downstream end of the shaft 36 twist the predetermined angle in the direction of rotation with respect to the downstream end of the shaft 38, the apertures 46 and 50 in the limb 44 of the flange 42 and the portion 48 of the shaft 38 respectively align with each other and allow oil to flow from the shaft 38 into the bearing housing.
This leakage of oil from the shaft 38 causes oil in the pipe 58 on the side of the restrictor 58 remote from the oil supply, and oil in the chamber 70 and pipe 63 to flow to the shaft 38. The restrictor 58 controls the flow of oil along the pipe 56 to the shaft 38 and chamber 70, and causes a change in the pressure difference across the restrictor 58, and the piston 66 senses this change in the pressure difference and moves to a new position.
The movement of the piston 66 may be used to shut off a supply of fuel to the gas turbine engine
10. The arm 72 of the piston 66 may be used to operate a servo system which is used to shut off the supply of fuel to the gas turbine engine 10.
The restrictor 58 is chosen to allow a constant flow of oil to the shaft 38 sufficient for efficient
lubrication of the bearings.
Figure 5 shows a sensing means 78 and part of
an alternative oil supply system. Oil from an oil
supply is supplied through pipes 80 and 82 to the
tube 52 and the shaft 38. A pipe 84 which has a restrictor 86 and a closed end extends from pipe 80.
A pipe 88 leads from the pipe 82 to a chamber 96 formed on one side of a piston 94 positioned within a cylinder 92, and a pipe 90 extends from the pipe 84 on one side of the restrictor 86 remote from the pipe 84 on one side of the restrictor 86 remote from the pipe 80 to a chamber 98 formed on the other side of the piston 94. An arm 100 which extends through the wall of the cylinder 92 from the piston 94 is connected to a fuel shut off system.
In normal operation oil flows from the oil supply through pipes 80 and 82 to the tube 52 and the bearings. A portion of the oil flows from pipe 80 into pipe 84 and through the restrictor 86 and the pipe 90 into the chamber 98, another portion of oil flows from pipe 82 through pipe 88 into chamber 96. The piston 94 in the cylinder 92 is an equilibrium position as shown in figure 5 as the pressure of the oil in the chambers 96 and 98 is equal.
But when the apertures 46 and 50 in the limb 44 of the flange 42 and the portion 48 of the shaft 38 respectively align with each other oil flows from the pipe 84 remote from the oil supply into the bearing housing. This leakage of oil from the shaft results in a change in the pressure difference between the oil in the pipe 54 at the side of the restrictor 86 remote from pipe 80 and the oil in pipe 82. The piston 94 senses the difference in pressure and moves to a new position, and the movement of the piston 94 and the associated arm 100 may be used to operate a servo system which will shut off the supply of fuel to the gas turbine engine 10.
It may be possible to use other means to sense a change in the pressure difference across the restrictor, and many different servo systems may be installed in the system and operated by a sensing means to cause the supply of fuel to the gas turbine engine to be terminated.
Claims (12)
1. A gas turbine engine which comprises a first shaft positioned coaxially within a second shaft, one of the shafts drivingly connects a first rotating
assembly to a second rotating assembly, a portion of the first shaft having an outer diameter substantially the same as an inner diameter of the
second shaft, a fluid supply means to supply fluid to the first shaft, means to detect when a relative
angular displacement between the shaft reaches a
predetermined value when the gas turbine engine
is in operation, said detecting means comprises at
least one aperture in the said portion of the first
shaft and a corresponding aperture in the second
shaft, the apertures in the first and second shaft
lying in the same plane, the aperture in the first
shaft being positioned a predetermined angle in
the direction of rotation of the shafts from the
aperture in the second shaft, in operation when
the relative angular displacement between the
first and second shafts reaches the predetermined
value the apertures in the first and second shafts aligning with each other permitting said fluid to flow out of the first shaft.
2. A gas turbine engine as claimed in claim 1 in which the said portion of the first shaft has a plurality of equi-spaced apertures and the second shaft has an equal number of equi-spaced apertures, the apertures in the first and second shafts lying in the same plane and each aperture in the first shaft being positioned a predetermined angle in the direction of rotation of the shafts from the corresponding aperture in the second shaft, in operation when the relative angular displacement between the first and second shaft reaches the predetermined value the apertures in the first and second shafts aligning with each other permitting the fluid to flow out of the first shaft.
3. A gas turbine engine as claimed in claim 1 or claim 2 in which the second shaft drivingly connects the first rotating assembly to the second rotating assembly, the first shaft extending the full length of the second shaft and the first shaft being secured to the upstream end of the second shaft, the said portion of the first shaft and the apertures in the first and second shafts being positioned at the downstream end of the first and second shafts respectively, in operation the twisting of the second shaft causing the downstream end of the second shaft to be angularly displaced relative to the downstream end of the first shaft.
4. A gas turbine engine as claimed in any of claims 1 to 3 in which the fluid supply means comprises a restrictor, means to sense a change in pressure difference between the pressure of the fluid on either side of the restrictor when the apertures in the first and second shafts are in alignment with each other permitting fluid to flow out of the first shaft.
5. A gas turbine engine as claimed in claim 4 in which the sensing means comprises a piston which is positioned within and forms a first and a second chamber with a cylinder, the first chamber receiving fluid from the fluid supply means from a position on one side of the restrictor and the second chamber receiving fluid from the fluid supply means from a position on the other side of the restrictor, the piston sensing a change in pressure difference between the pressure of the fluid on either side of the restrictor, the piston moving in the cylinder when there is a change in pressure difference between the pressure of the fluid on either side of the restrictor.
6. A gas turbine engine as claimed in claims 4 or 5 in which a fuel supply is arranged to supply fuel to the gas turbine engine, the sensing means supplying an operating signal to an operating means which causes the supply of fuel to the gas turbine engine to be at least reduced when the sensing means senses a change in pressure difference between the pressure of the fluid on either side of the restrictor.
7. A gas turbine engine as claimed in claim 6 in which the piston has an arm which moves with the piston when there is a change in pressure difference between the pressure of the fluid on either side of the restrictor, the movement of the arm transmitting an operating signal to an operating means which causes the supply of fuel to the gas turbine engine to be at least reduced.
8. A gas turbine engine as claimed in claims 6 or 7 in which the operating means causes the supply of fuel to the gas turbine engine to be terminated.
9. A gas turbine engine as claimed in any of claims 6 to 8 in which the operating means is a fuel servo system.
10. A gas turbine engine as claimed in any of claims 1 to 9 in which the fluid is oil.
11. A gas turbine engine as claimed in any of claims 1 to 10 in which a portion of the fluid supplied to the first shaft shows through the first shaft and is used to lubricate at least one bearing of the first or second shafts.
12. A gas turbine engine substantially as herein described and with reference to Figures 1 to 4 of the accompanying drawings.
1 3. A gas turbine engine substantially as herein described and with reference to Figure 5 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08219698A GB2123568A (en) | 1982-07-07 | 1982-07-07 | Measuring torque on gas- turbine engine shafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08219698A GB2123568A (en) | 1982-07-07 | 1982-07-07 | Measuring torque on gas- turbine engine shafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2123568A true GB2123568A (en) | 1984-02-01 |
Family
ID=10531532
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08219698A Withdrawn GB2123568A (en) | 1982-07-07 | 1982-07-07 | Measuring torque on gas- turbine engine shafts |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2123568A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3046841A1 (en) * | 2016-01-20 | 2017-07-21 | Turbomeca | TORSION COUPLEMETER |
| EP3435058A1 (en) * | 2017-07-28 | 2019-01-30 | Rolls-Royce Deutschland Ltd & Co KG | Assembly and method for detecting a break in a shaft |
| US10465554B2 (en) | 2015-01-05 | 2019-11-05 | Rolls-Royce Plc | Turbine engine shaft break detection |
-
1982
- 1982-07-07 GB GB08219698A patent/GB2123568A/en not_active Withdrawn
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10465554B2 (en) | 2015-01-05 | 2019-11-05 | Rolls-Royce Plc | Turbine engine shaft break detection |
| FR3046841A1 (en) * | 2016-01-20 | 2017-07-21 | Turbomeca | TORSION COUPLEMETER |
| WO2017125671A1 (en) * | 2016-01-20 | 2017-07-27 | Safran Helicopter Engines | Twisting torque sensor |
| CN108431370A (en) * | 2016-01-20 | 2018-08-21 | 赛峰直升机发动机公司 | Torsional moment sensor |
| CN108431370B (en) * | 2016-01-20 | 2020-11-17 | 赛峰直升机发动机公司 | Torsional moment sensor |
| EP3435058A1 (en) * | 2017-07-28 | 2019-01-30 | Rolls-Royce Deutschland Ltd & Co KG | Assembly and method for detecting a break in a shaft |
| US10655493B2 (en) | 2017-07-28 | 2020-05-19 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement, turbo engine and method for the recognition of a shaft breakage of a shaft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |