Gas turbine engine and a rotor for a gas turbine engine

• US 7,507,070 B2
• Filed: 07/25/2005
• Issued: 03/24/2009
• Est. Priority Date: 03/27/1999
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Jones, Alan R
• Primary Examiner(s): Verdier; Christopher
• Application Number:
  US11/188,092
• Publication Number:
  US 20070031249A1
• Time in Patent Office: 1,338 Days
• Field of Search: 415/200, 415/216.1, 415176-178, 416/241.R, 416/241.A, 416/229.A, 416/244.R, 416/244.A
• US Class Current: 415/200
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• CPC Class Codes: F01D 19/00 Starting of machines or engines; Regulating, controlling, or safety means in connection therewith warming-up before starting F01D25/10; turning or inching gear F01D25/34
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/584 cooling or heating the machine F04D29/5846, F04D29/5853 take precedence
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: F05D 2300/141 Silver
• CPC Class Codes: F05D 2300/142 Gold
• CPC Class Codes: F05D 2300/224 Carbon, e.g. graphite
• CPC Class Codes: F05D 2300/504 Reflective properties
• CPC Class Codes: F05D 2300/611 Coating

Abstract

A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Claims

1. A rotor for a gas turbine engine having a radially inner surface, a radially outer surface, an upper portion and a lower portion, said rotor having a high emissivity surface finish on a portion of its radially outer surface, said rotor having a low emissivity surface finish on a portion of its radially outer surface, said rotor having a high emissivity surface finish on a portion of its radially inner surface, said rotor having a low emissivity surface finish on a portion of its radially inner surface to reduce temperature differentials between the upper portion and the lower portion of the rotor.

2. A gas turbine engine comprising a low-pressure rotor, a high pressure rotor and at least one casing, said high pressure rotor being arranged coaxially around a low-pressure turbine, the at least one casing being arranged coaxially around said high-pressure rotor, said high-pressure rotor having a radially inner surface, a radially outer surface, an upper portion and a lower portion, said low-pressure rotor having a radially inner surface, a radially outer surface, an upper portion and a lower portion, the at least one casing having a radially inner surface and a radially outer surface, said high-pressure rotor having a high emissivity surface finish on a portion of its radially outer surface, said high-pressure rotor having a low emissivity surface finish on a portion of its radially outer surface, said high-pressure rotor having a high emissivity surface finish on a portion of its radially inner surface, said high-pressure rotor having a low emissivity surface finish on a portion of its radially inner surface to reduce temperature differentials between the upper portion and the lower portion of the high-pressure rotor.

3. A gas turbine engine as claimed in claim 2 wherein the low-pressure rotor has a high emissivity surface finish on its radially outer surface.

4. A gas turbine engine as claimed in claim 2 wherein the at least one casing has a low emissivity surface finish on its radially inner surface.