Systems and methods for changing a speed of a compressor boost stage in a gas turbine

• US 9,328,667 B2
• Filed: 06/19/2015
• Issued: 05/03/2016
• Est. Priority Date: 11/29/2011
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: MacFarlane, Ian A.
• Primary Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US14/744,323
• Publication Number:
  US 20150285156A1
• Time in Patent Office: 319 Days
• US Class Current: 1/1
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F04D 19/026 with a plurality of shafts rotating at different speeds F04D19/022 takes precedence
• CPC Class Codes: F04D 25/02 Units comprising pumps and their driving means
• CPC Class Codes: F04D 27/0261 by varying driving speed
• CPC Class Codes: F05D 2260/4023 through a friction clutch
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/902 using frictional mechanical forces
• CPC Class Codes: F23R 3/26 Controlling the air flow
• CPC Class Codes: Y02B 30/70 Efficient control or regulation technologies, e.g. for control of refrigerant flow, motor or heating

Abstract

Systems and methods for changing a speed ratio between a compressor boost stage (12) and at least one power turbine (16) of a gas turbine engine (10) are described. Such a system may comprise a coupling device (20) configured to selectively transmit energy from the at least one power turbine (16) to the boost stage (12) according to at least a first speed ratio and a second speed ratio. The system may also comprise an auxiliary power device (22, 26) configured to cause a rotational speed of the boost stage (12) to change from a first speed corresponding substantially to the first speed ratio to a second speed corresponding substantially to the second speed ratio when the boost stage (12) is decoupled from the at least one power turbine (16).

Claims

1. A method for changing a rotational speed of a compressor boost stage driven by at least one power turbine of a gas turbine engine relative to a speed of the at least one power turbine, the method comprising:

driving the boost stage at a first rotational speed corresponding to a first speed ratio between the boost stage and the at least one power turbine via coupling between the boost stage and the at least one power turbine;

decoupling the boost stage from the at least one power turbine;

changing the rotational speed of the boost stage from the first rotational speed to a second rotational speed substantially corresponding to a second speed ratio between the boost stage and the at least one power turbine;

re-coupling the boost stage to the at least one power turbine at the second speed ratio; and

driving the boost stage at the second rotational speed via coupling between the boost stage and the at least one power turbine.

2. The method as defined in claim 1, comprising transferring energy to the boost stage to cause the rotational speed of the boost stage to increase in relation to the at least one power turbine while the boost stage is decoupled from the at least one power turbine.

3. The method as defined in claim 1, comprising adjusting at least one of inlet guide vanes and a bleed valve to adjust a resistance on the boost stage.

4. The method as defined in claim 2, comprising extracting pressurized air from a core section of the turbine engine and using the pressurized air to drive an air turbine coupled to the boost stage to cause the rotational speed of the boost stage to increase in relation to the at least one power turbine.

5. The method as defined in claim 4, comprising pressurizing the air extracted from the core section prior to driving the air turbine.

6. The method as defined in claim 1, comprising braking the boost stage to cause the rotational speed of the boost stage to decrease in relation to the at least one power turbine while the boost stage is decoupled from the at least one power turbine.