# US 10,865,761 B2 · Igniter for gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,865,761 B2 - Document ID: US10865761B2 - Status: Granted - Kind: B2 - Application number: 16/369,741 - Filed: 2019-03-29 - Published: 2020-03-12 - Granted: 2020-12-15 - Earliest claimed: 2018-09-12 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Richard Freer; Kian McCaldon; Tin-Cheung John Hu; Michel Bousquet; André Fortin - Web page: https://patentgrep.com/patent/US10865761B2 ## CPC - F02P 19/02: electric, e.g. layout of circuits of apparatus having glowing plugs - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F02C 7/266: Electric (sparking plugs H01T) - F23D 11/446: {heated by an auxiliary flame} - F23Q 7/001: {Glowing plugs for internal-combustion engines} - F23R 3/18: Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants - F23R 3/30: comprising fuel prevapourising devices - F23D 2207/00: Ignition devices associated with burner - F23R 2900/00015: Trapped vortex combustion chambers - F02P: IGNITION, OTHER THAN COMPRESSION IGNITION, FOR INTERNAL-COMBUSTION ENGINES; TESTING OF IGNITION TIMING IN COMPRESSION-IGNITION ENGINES ({anti-pollution means for internal-combustion engines F02B17/00}; specially adapted for rotary-piston or oscillating-piston engines F02B53/12; {ignition of gas turbine plants F02C7/26; ignition of jet propulsion plants F02K9/95; starting of combustion engines F02N9/00}; ignition of combustion apparatus in general, glowing plugs F23Q; measuring of physical variables in general G01; controlling in general G05; data processing in general G06; electrical components in general see Section H; {ignition coils H01F38/12}; sparking plugs H01T13/00) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F23D: BURNERS - F23Q: IGNITION (devices or installations peculiar to internal-combustion engines F02P; of cigarettes or tobacco A24F; compositions therefor, chemical igniters C06C); EXTINGUISHING-DEVICES ## Abstract There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod. ## Claims ### Claim 1 An igniter for a gas turbine engine comprising: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver extending axially between a closed end proximate the base and an open end proximate the rod end, the igniter seated from a fuel source of the gas turbine engine but for at the open end of the fuel receiver, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod. ### Claim 2 (depends on 1) The igniter of claim 1, wherein the fuel receiver is delimited by an inner surface of a sleeve surrounding the heater rod. ### Claim 3 (depends on 2) The igniter of claim 2, wherein the sleeve extends circumferentially around the heater rod along at least a portion of a length of the heater rod. ### Claim 4 (depends on 2) The igniter of claim 2, wherein the inner surface of the sleeve extends circumferentially around the heater rod along at least a portion of a length of the heater rod, said sleeve having a plurality of fins. ### Claim 5 (depends on 1) The igniter of claim 1, wherein the heater rod has a heating section axially extending along between opposite ends of a heater contained within the heater rod, the heating section protruding axially from the fuel receiving portion located closest to the heating section. ### Claim 6 (depends on 5) The igniter of claim 5, wherein the fuel receiving portion located closest to the heating section is a portion of a sleeve which is remote from the base and radially closest to the heating section. ### Claim 7 (depends on 6) The igniter of claim 6, wherein a distance along the axis between the rod end and the fuel receiver portion located closest to the rod end is less or equal to two times a length of the heating section. ### Claim 8 (depends on 7) The igniter of claim 7, wherein the distance is less or equal to one and a half times the length of the heating section. ### Claim 9 (depends on 7) The igniter of claim 7, wherein the distance corresponds to the length of the heating section. ### Claim 10 (depends on 7) The igniter of claim 7, wherein the distance is about half the length of the heating section. ### Claim 11 (depends on 7) The igniter of claim 7, wherein the distance is about a quarter of the length of the heating section. ### Claim 12 (depends on 1) The igniter of claim 1, wherein the fuel receiver portion located closest to the heating section is spaced apart from the heater rod by a gap. ### Claim 13 (depends on 1) The igniter of claim 1, wherein the fuel receiver portion located closest to the heating section is made of metal. ### Claim 14 (depends on 1) The igniter of claim 1, further comprising a sleeve extending circumferentially around the heater rod along at least a portion of a length of the heater rod, the sleeve structurally connected to the base and protruding along the axis from the base towards the rod end, the fuel receiver being provided at an end of the sleeve remote from the base. ### Claim 15 (depends on 1) The igniter of claim 1, wherein the fuel receiver has a portion connected to the heater rod between the rod end and the base. ### Claim 16 (depends on 1) The igniter of claim 1, wherein the base includes a body of a glow plug, the glow plug including the heater rod and at least a casing portion of an adaptor, the casing portion of the adaptor connected to the body of the glow plug around the body of the glow plug. ### Claim 17 (depends on 16) The igniter of claim 16, wherein the fuel receiver forms part of the casing portion of the adaptor. ### Claim 18 (depends on 16) The igniter of claim 16, wherein the adaptor further comprises a liner portion configured to be matingly connected to a liner of the gas turbine engine, the fuel receiver being defined by the liner portion. ### Claim 19 (depends on 1) The igniter of claim 1, wherein a portion of an outer surface of the base is threaded for engaging a correspondingly threaded aperture of a casing of the gas turbine engine. ### Claim 20 A gas turbine engine comprising: an inner liner and an outer liner defining a combustion chamber between the inner liner and the outer liner, one of the inner liner and the outer liner defining an igniter hole; and an igniter received within the igniter hole, the igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod and protruding beyond the one of the inner liner and the outer liner into the combustion chamber.