Patent USRE23433E successfully refreshed from Google Patents.
Patent EP0810405A2 successfully refreshed from Google Patents.
EP0810405A2
Expired / Lapsed
EP
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A gas turbine engine combustion chamber and a method of operation thereof
Assignee: Rolls Royce PLC
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Filing: 1997-04-23
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Granted: —
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Expires: 2017-04-23
Abstract
Abstract A gas turbine engine combustion chamber (28) comprises a primary combustion zone (36) and a secondary combustion zone (40) downstream of the primary combustion zone (36). A catalytic combustion zone (44) is arranged downstream of the secondary combustion zone (40) and a homogeneous combustion zone (100) is arranged downstream of the catalytic combustion zone (44). A pilot injector (62) supplies fuel into the primary combustion zone (36). At least one primary premixing duct (54,56) has a plurality of primary fuel injectors (58,60) to supply a first mixture of fuel and air into the primary combustion zone (36). A secondary premixing duct (64) has a plurality of secondary fuel injectors (82) to supply a second mixture of fuel and air into the secondary combustion zone (40). A plurality of temperature sensors (102) are arranged at the intake to the catalytic combustion zone (44) and a processor (104) controls the valves (106,108,110) which adjust the supply of fuel the fuel injectors (58,60,62,82) to ensure that the temperature at the intake to the catalytic combustion zone (44) remains in a predetermined temperature range.
Inventors
- 👤 Jeffrey Douglas Willis
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-05 23:57
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/34; F23R3/40; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/08; F05D2270/083
Claims Analysis
Total Claims: 21
Claim 1
Independent Claim
182 words
A gas turbine engine combustion chamber (28) comprising a primary combustion zone (36), a secondary combustion zone (40) downstream of the primary combustion zone (36), a pilot fuel injector (62) to supply fuel into the primary combustion zone (36), at least one primary premixing duct (54,56) to supply a first mixture of fuel and air into the primary combustion zone (36), at least one secondary premixing duct (64) to supply a second mixture of fuel and air into the secondary combustion zone (40), the primary premixing duct (54,56) has air inlet means to supply air into the primary premixing duct (54,56) and primary fuel injector means (58,60) to supply fuel into the primary premixing duct (54,56), the secondary premixing duct (64) has air inlet means (74) to supply air into the secondary premixing duct (64) and secondary fuel injector means (82) to supply fuel into the secondary premixing duct (64), characterised in that a catalytic combustion zone (44) is arranged downstream of the secondary combustion zone (40) and a homogeneous combustion zone (100) is arranged downstream of the catalytic combustion zone (44).
Claim 2
Dependent Claim
135 words
A gas turbine engine combustion chamber as claimed in claim 1 wherein valve means (106,108,110) are provided to control the flow of fuel to the pilot fuel injector (62), the primary fuel injector means (58,60) and the secondary fuel injector means (82), at least one temperature sensor (102) is arranged at the upstream end (94) of the catalytic combustion zone (44) to measure the temperature at the upstream end of the catalytic combustion zone (44) and a processor (104) is electrically connected to the temperature sensor (102) so as to receive a measure of the temperature detected by the temperature sensor (102), and the processor (104) is arranged to control the valve means (106,108,110) such that the temperature at the upstream end (94) of the catalytic combustion zone (44) remains in a predetermined temperature range.
Claim 3
Dependent Claim
27 words
A gas turbine engine combustion chamber as claimed in claim 1 or claim 2 wherein stabiliser means (112) are provided downstream of the catalytic combustion zone (44).
Claim 4
Dependent Claim
27 words
A gas turbine engine combustion chamber as claimed in claim 3 wherein the stabiliser means (112) comprises an increase in cross-sectional area of a transition duct (96).
Claim 5
Dependent Claim
22 words
A gas turbine engine combustion chamber as claimed in any of claims 1 to 4 wherein the combustion chamber (28) is tubular.
Claim 6
Dependent Claim
25 words
A gas turbine engine combustion chamber as claimed in any of claims 1 to 5 wherein there are a plurality of primary premixing ducts (54,56).
Claim 7
Dependent Claim
25 words
A gas turbine engine combustion chamber as claimed in claim 6 wherein the primary premixing ducts (54,56) are defined by at least one swirler assembly.
Claim 8
Dependent Claim
24 words
A gas turbine engine combustion chamber as claimed in claim 7 wherein the at least one swirler assembly is a radial flow swirler assembly.
Claim 9
Dependent Claim
24 words
A gas turbine engine combustion chamber as claimed in any of claims 1 to 8 wherein there is a single secondary premixing duct (64).
Claim 10
Dependent Claim
19 words
A gas turbine engine combustion chamber as claimed in claim 9 wherein the secondary premixing duct (64) is annular.
Claim 11
Dependent Claim
20 words
A gas turbine engine combustion chamber as claimed in claim 2 wherein there are a plurality of temperature sensors (102).
Claim 12
Dependent Claim
34 words
A gas turbine engine combustion chamber as claimed in claim 2 or claim 11 wherein the at least one temperature sensor (102) is located in the intakes (94) of the catalytic combustion zone (44).
Claim 13
Dependent Claim
27 words
A gas turbine engine combustion chamber as claimed in claim 2, claim 11 or claim 12 wherein the at least one temperature sensor (102) comprises a thermocouple.
Claim 14
Independent Claim
296 words
A method of operating a gas turbine engine combustion chamber (28) comprising a primary combustion zone (36), a secondary combustion zone (40) downstream of the primary combustion zone (36), a pilot fuel injector (62) to supply fuel into the primary combustion zone (36), at least one primary premixing duct (54,56) to supply a first mixture of fuel and air into the primary combustion zone (36), at least one secondary premixing duct (64) to supply a second mixture of fuel and air into the secondary combustion zone (40), the primary premixing duct (54,56) has air inlet means to supply air into the primary premixing duct (54,56) and primary fuel injector means (58,60) to supply fuel into the primary premixing duct (36), the secondary premixing duct (64) has air inlet means to supply air into the secondary premixing duct (64) and secondary fuel injector means (82) to supply fuel into the secondary premixing duct (64), a catalytic combustion zone (44) downstream of the secondary combustion zone (40) and a homogeneous combustion zone (100) downstream of the catalytic combustion zone (44), the method comprising (a) supplying fuel to the first combustion zone (36) from the pilot fuel injector (62) in a first mode of operation, (b) supplying fuel to the first combustion zone (36) from the pilot fuel injector (62) and supplying fuel to the second combustion zone (40) from the secondary fuel injector means (82) through the secondary premixing duct (64) in a second mode of operation, and (c) supplying fuel to the primary combustion zone (36) from the primary fuel injector means (58,60) through the primary premixing duct (54,56) and supplying fuel to the secondary combustion zone (40) from the secondary fuel injector means (82) through the secondary premixing duct (64) in a third mode of operation.
Claim 15
Dependent Claim
88 words
A method as claimed in claim 14 wherein the method comprises measuring the temperature at the upstream end of the catalytic combustion zone (44), determining if the temperature at the upstream end of the catalytic combustion (44) is within a predetermined temperature range and controlling the flow of fuel to the pilot fuel injector (62), the primary fuel injector means (58,60) and the secondary fuel injector means (82) such that the temperature at the upstream end of the catalytic combustion zone (44) remains in the predetermined temperature range.
Claim 16
Dependent Claim
24 words
A method of operating a gas turbine engine combustion chamber as claimed in claim 15 wherein the predetermined temperature range is 650°C to 850°C.
Claim 17
Dependent Claim
73 words
A method of operating a gas turbine engine combustion chamber as claimed in claim 15 or claim 16 wherein the method comprises controlling the flow of fuel to the primary fuel injector means (58,60) and the secondary fuel injector means (82) in the third mode of operation such that the temperature at the upstream end (94) of the catalytic combustion zone (44) is substantially at the minimum temperature within the predetermined temperature range.
Claim 18
Dependent Claim
160 words
A gas turbine engine combustion chamber (28) comprising a catalytic combustion zone (44) and a homogeneous combustion zone (100) downstream of the catalytic combustion zone (44), at least one fuel injector (58,60,62,82) to supply fuel to the combustion chamber (28) upstream of the catalytic combustion zone (44), valve means (106,108,110) are provided to control the flow of fuel to the at least one fuel injector (58,60,62,82) characterised in that at least one temperature sensor (102) is arranged at the upstream end of the catalytic combustion zone (44) to measure the temperature at the upstream end of the catalytic combustion zone (44) and a processor (104) is electrically connected to the temperature sensor (102) so as to receive a measure of the temperature detected by the temperature sensor (102) and the processor (104) is arranged to control the valve means (106,108,110) such that the temperature at the upstream end of the catalytic combustion zone (44) remains in a predetermined temperature range.
Claim 19
Dependent Claim
171 words
A gas turbine engine combustion chamber as claimed in claim 18 wherein the combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) downstream of the primary combustion zone (36), a pilot fuel injector (62) to supply fuel into the primary combustion zone (36), at least one primary premixing duct (54,56) to supply a first mixture of fuel and air into the primary combustion zone (36), at least one secondary premixing duct (64) to supply a second mixture of fuel and air into the secondary combustion zone (40), the primary premixing duct (54,56) has air inlet means to supply air into the primary premixing duct (54,56) and primary fuel injector means (58,60) to supply fuel into the primary premixing duct (54,56), the secondary premixing duct (64) has air inlet means to supply air into the secondary premixing duct (64) and secondary fuel injector means (82) to supply fuel into the secondary premixing duct (40), the catalytic combustion zone (44) is downstream of the secondary combustion zone (40).
Claim 20
Dependent Claim
40 words
A gas turbine engine combustion chamber as claimed in claim 18 wherein the valve means (106,108,110) controls the flow of fuel to the pilot fuel injector (62), the primary fuel injector means (58,60) and the secondary fuel injector means (82).
Claim 21
Dependent Claim
32 words
A gas turbine engine combustion chamber as claimed in claim 2 wherein at lease one temperature sensor (118) is arranged to measure the temperature of the air supplied to the combustion chamber.
References Cited (Backward Citations)
No citation records indexed.
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