GAS TURBINE ENGINE

• US 20150101331A1
• Filed: 09/16/2014
• Published: 04/16/2015
• Est. Priority Date: 10/10/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: PEACE, Richard, GOULDS, Robert, LACE, Brian Richard
• Granted Patent: US 10,024,242 B2
• Time in Patent Office: Days
• US Class Current: 60/722
• CPC Class Codes: F01D 25/08 Cooling of machines or engines in general F01P; Heating; Heat-insulation of blade-carrying members, of blades F01D5/00
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F01D 25/145 Thermally insulated casings
• CPC Class Codes: F02C 3/14 characterised by the arrangement of the combustion chamber in the plant combustion chambers per se F23R; F02C3/205 takes precedence
• CPC Class Codes: F02C 6/04 Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output F02C6/18 takes precedence ; for a fluidised-bed combustor F02C3/205
• CPC Class Codes: F02C 6/06 providing compressed gas F02C6/10 takes precedence
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F02C 7/125 by partial arc admission of the working fluid or by intermittent admission of working and cooling fluid
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 7/24 Heat or noise insulation air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00
• CPC Class Codes: F02C 7/25 Fire protection or prevention in general A62
• CPC Class Codes: F02C 7/28 Arrangement of seals
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/50 Kinematic linkage, i.e. transmission of position
• CPC Class Codes: F16C 1/10 Means for transmitting linear movement in a flexible sheathing, e.g. "Bowden-mechanisms" guiding-sheathings F16C1/26
• CPC Class Codes: F16C 1/103 to a hole in the wall or bracket
• CPC Class Codes: F16C 1/262 End fittings; Attachment thereof to the sheathing or tube
• CPC Class Codes: F16C 2360/23 : Gas turbine engines in general F02C
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine having a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use. The gas turbine also has an actuator that is located in the first zone and is configured to generate a mechanical force when operated, an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force and a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall. The mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device.

Claims

1. A gas turbine engine having:

a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use;

an actuator that is located in the first zone and is configured to generate a mechanical force when operated;

an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force;

a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall, wherein;

the mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device;

the mechanical force transmitting device includes an elongate element configured to move along a linear path so as to transmit a mechanical force generated by the actuator to the actuatable device, and an elongate housing/shell, the elongate element being configured to move along a linear path within the elongate housing/shell; and

the gas turbine engine includes an off-take device for extracting cooling air from an airflow in the gas turbine engine and for supplying the extracted cooling air to be guided into the elongate housing/shell when the gas turbine engine is in use.

2. A gas turbine engine according to claim 1, wherein the second zone has a temperature of 300°

C. or higher when the gas turbine engine is in use.

3. A gas turbine engine according to claim 1 wherein the elongate element is a flexible cable.

4. A gas turbine engine according to claim 1, wherein the off-take device is configured so that the extracted cooling air is at a pressure that is higher than the static pressure of the airflow.

5. A gas turbine engine according to claim 1, wherein the off-take device has:

a first passage that extends from an inlet to an outlet in the direction of the airflow, wherein the cross-sectional area of the first passage, as measured in a direction perpendicular to the direction of airflow, increases and then decreases as the passage progresses in the direction of the airflow;

a second passage for extracting the portion of air from the airflow, wherein the second passage has an inlet that is a hole formed in a sidewall of the first passage between the inlet and outlet of the first passage.

6. A gas turbine engine according to claim 1, wherein the elongate housing/shell includes a coolant dumping device for allowing spent coolant to exit the elongate housing/shell in the second zone

7. A gas turbine engine according to claim 1 wherein the gas turbine engine includes a sealing unit which seals the hole in the fire wall.

8. A gas turbine engine according to claim 7 wherein the sealing unit include a primary seal and a secondary seal for inhibiting/preventing coolant from flowing out of the sealing unit into the first zone.

9. A gas turbine engine according to claim 1 wherein each zone is configured to have a continual flow of air running through the zone when the gas turbine engine is in use.

10. A gas turbine engine having:

a fire wall that is configured to provide a fire resistant barrier between a first zone and a second zone in the gas turbine engine, the second zone being hotter than the first zone when the gas turbine engine is in use;

an actuator that is located in the first zone and is configured to generate a mechanical force when operated;

an actuatable device that is located in the second zone and is configured to be actuated by a mechanical force;

a mechanical force transmitting device that extends from the actuator to the actuatable device via a hole in the fire wall, wherein;

the mechanical force transmitting device is configured to, when the actuator is operated, actuate the actuatable device by transmitting a mechanical force generated by the actuator to the actuatable device; and

the mechanical force transmitting device is a flexible cable.

11. An off-take device for extracting air from an airflow in the gas turbine engine at a pressure that is higher than the static pressure of the airflow, wherein the off-take device has:

a first passage that extends from an inlet to an outlet in the direction of the airflow, wherein the cross-sectional area of the first passage, as measured in a direction perpendicular to the direction of airflow, increases and then decreases as the first passage progresses in the direction of the airflow;

a second passage for extracting air from the airflow, wherein the second passage has an inlet that is a hole formed in a sidewall of the first passage between the inlet and outlet of the first passage.