Gas turbine engines

• US 4,473,998 A
• Filed: 06/14/1983
• Issued: 10/02/1984
• Est. Priority Date: 06/30/1982
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: King, Peter R.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Stout, Donald E.
• Application Number:
  US06/504,307
• Time in Patent Office: 476 Days
• Field of Search: 60/39.091, 60/39.75, 74/577 R, 74/577 S, 415/9, 415/122 R, 415/118, 137/38, 137/45
• US Class Current: 60/39.091
• CPC Class Codes: F01D 21/04 responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
• CPC Class Codes: F02C 9/46 Emergency fuel control
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 74/2137 Single tooth

Abstract

A detection means to detect when a relative angular displacement between a first shaft and a second shaft of a gas turbine engine reaches a predetermined value comprises an aperture in the first shaft and a cooperating ratchet device attached to the second shaft. An arm of the ratchet device abuts the circumference of the first shaft, and the aperture in the first shaft is initially positioned a predetermined angle in the direction of rotation of the shafts from the arm. In operation when the relative angular displacement between the shafts reaches the predetermined value the arm of the ratchet device aligns with and moves into the aperture in the first shaft.

The ratchet device has a pawl which moves radially outwards from the shaft and engages with and displaces a lever when the arm moves into the aperture. The displacement of the lever may be used to shut off the supply of fuel to the gas turbine engine or to operate an indication means.

Claims

1. A gas turbine engine which comprises a first shaft positioned coaxially within a second shaft, one of the shafts drivingly connecting a first rotating asssembly to a second rotating assembly, and a means to detect when a relative angular displacement between the shafts reaches a predetermined value while the gas turbine engine is in operation, said means comprising at least one aperture in the first shaft and a corresponding ratchet device mounted on a spindle which is attached to the second shaft, the ratchet device having an arm positioned at one end which abuts the circumference of the first shaft;

the aperture in the first shaft lying in the same plane as the ratchet device and positioned at a pre-determined angle in the direction of rotation of the shafts from the arm of the ratchet device;

in operation when the relative angular displacement between the first and second shafts reaches the pre-determined value the arm of said ratchet device aligns with and moves into said aperture.

2. A gas turbine engine as claimed in claim 1 in which the first shaft has a plurality of equi-spaced apertures and the second shaft has an equal number of equi-spaced ratchet devices mounted on spindles, the apertures in the first shaft and the ratchet devices 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 arm of a corresponding ratchet device;

in operation when the relative angular displacement between the first and second shafts reaches the predetermined value the arm of each ratchet device aligns with and moves into the corresponding aperture in the first shaft.

3. A gas turbine engine as claimed in claim 2 in which the second shaft drivingly connects the first rotating assembly to the second rotating assembly, the first shaft extends the full length of the second shaft and the first shaft is secured to the upstream end of the second shaft, the apertures in the first shaft and the corresponding ratchet devices are 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.

4. A gas turbine engine as claimed in claim 2 in which the first shaft drivingly connects the first rotating assembly to the second rotating assembly, at least one weight being positioned radially between and attached to the first and second shafts respectively;

the weight is attached to the first and second shafts by a pair of links which allow the weight to move in a radial direction;

in operation the weight moves radially outwards and causes the second shaft to be angularly displaced relative to the first shaft.

5. A gas turbine engine as claimed in claim 1, in which each ratchet device has a pawl positioned at the opposite end to the arm, an operating means being spaced radially outwards from the pawl;

in operation when the arm of each ratchet device moves into the corresponding aperture in the first shaft each ratchet device rotates about its spindle and each pawl moves radially outwards and as the shafts rotate one of the pawls engages with and causes displacement of the operating means.

6. A gas turbine engine as claimed in claim 5 in which a fuel supply is arranged to supply fuel to the gas turbine engine, the displacement of the operating means causing the supply of fuel to the gas turbine engine to be at least reduced.

7. A gas turbine engine as claimed in claim 6 in which the displacement of the operating means causes the supply of fuel to the gas turbine engine to be terminated.

8. A gas turbine engine as claimed in claim 5 including a means to indicate that the relative angular displacement between the shafts has reached the predetermined value, the displacement of the operating means causing the operation of the indication means.

9. A gas turbine engine as claimed in claim 5 in which the operating means is a lever or a cable.

10. A gas turbine engine as claimed in claim 2, in which each ratchet device has a pawl positioned at the opposite end to the arm, an operating means being spaced radially outwards from the pawl;

in operation when the arm of each ratchet device moves into the corresponding aperture in the first shaft each ratchet device rotates about its spindle and each pawl moves radially outwards and as the shafts rotate one of the pawls engages with and causes displacement of the operating means.

11. A gas turbine engine as claimed in claim 3, in which each ratchet device has a pawl positioned at the opposite end to the arm, an operating means being spaced radially outwards from the pawl;

in operation when the arm of each ratchet device moves into the corresponding aperture in the first shaft each ratchet device rotates about its spindle and each pawl moves radially outwards and as the shafts rotate one of the pawls engages with and causes displacement of the operating means.

12. A gas turbine engine as claimed in claim 4, in which each ratchet device has a pawl positioned at the opposite end to the arm, an operating means being spaced radially outwards from the pawl;

in operation when the arm of each ratchet device moves into the corresponding aperture in the first shaft each ratchet device rotates about its spindle and each pawl moves radially outwards and as the shafts rotate one of the pawls engages with and causes displacement of the operating means.