In-situ measurement of blade tip-to-shroud gap in turbine engine

Patent metadata

Field	Value
Publication number	US-10041371-B1
Application number	US-201514615487-A
Country	US
Kind code	B1
Filing date	Feb 6, 2015
Priority date	Feb 6, 2015
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A robotically articulated inspection scope (56, 69) inserted into a pilot fuel nozzle port (58) of a turbine engine (20) for in-situ measurement of gaps (59) between tips of turbine blades (40A) and the surrounding shroud (44). A non-contact gap measuring device (52) on a distal end (79) of the scope may be navigated through a combustor (28) and transition duct (34) into a position proximate a blade tip gap. The scope may be controlled via computer (68) via a robotic drive (66) affixed to the pilot fuel nozzle port. Multiple scopes may be used to measure gaps (59A-D) at multiple azimuths of the turbine simultaneously. The turbine disk (37) may be rotated on its operating turning gear to sequentially measure each blade at each azimuth. The computer may memorize an interactively navigated path for subsequent automated positioning.

First claim

The invention claimed is:

1. A method of inspecting a gap between a tip of a turbine blade and a surrounding gas path shroud in a gas turbine engine, comprising the steps of:
a) providing a robotically articulated inspection scope comprising a non-contact gap measuring device on a distal end thereof;
b) inserting the inspection scope into a pilot fuel port of a combustor of the gas turbine engine without separating halves of a casing of the engine;
c) robotically navigating the non-contact gap measuring device through the combustor and through a transition duct of the gas turbine engine to a position proximate a gap between a tip of a blade on a turbine disk and a surrounding gas path shroud in the gas turbine engine;
d) measuring the gap with the non-contact measuring device, and storing a width dimension of the gap in a computer;
e) rotating the turbine disk to position a next blade of the turbine disk proximate the non-contact measuring device;
f) repeating from steps d) and e) until gaps associated with a plurality of blades on the turbine disk have been measured;
sensing a temperature of the gas path shroud and the blade tip, respectively, during the measuring step;
wherein the non-contact gap measurement device comprises an infrared camera or thermocouple that senses the respective temperatures of the gas path shroud and the blade tip, and
wherein the first gap width is determined as a function of the respective temperatures.

2. The method of claim 1 , further comprising repeating steps d) and e) at a plurality of temperatures as the engine is cooled from an operating temperature to ambient following shutdown of the engine.

Assignees

• Siemens Energy Inc

Inventors

• Deascanis Joshua
• Letter David
• Bancalari Alejandro
• Hatcher Jr Clifford

Classifications

• F01D21/00

  Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• H04N7/18

  Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title