Method and apparatus for monitoring the temperature of the propulsion gas at the inlet to a high-performance turbine wheel

• US 4,744,670 A
• Filed: 05/05/1986
• Issued: 05/17/1988
• Est. Priority Date: 05/05/1986
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Janssen, John E.
• Primary Examiner(s): Cuchlinski, Jr., William A.
• Assistant Examiner(s): Will, Thomas B.
• Application Number:
  US06/859,666
• Time in Patent Office: 743 Days
• Field of Search: 374/143, 374/144, 374/148, 364/557, 364/431.02, 364/431.03, 318/417, 236/15 C
• US Class Current: 374/144
• CPC Class Codes: F01D 17/08 responsive to condition of working-fluid, e.g. pressure
• CPC Class Codes: F23N 2225/04 pressure
• CPC Class Codes: F23N 2225/08 temperature
• CPC Class Codes: F23N 2225/21 outlet temperature
• CPC Class Codes: F23N 2241/20 Gas turbines
• CPC Class Codes: F23N 5/022 using electronic means F23N5/04 - F23N5/14 take precedence
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/46 Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
• CPC Class Codes: G01K 13/02 for measuring temperature of moving fluids or granular materials capable of flow
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An apparatus is disclosed for monitoring the temperature of the propulsion gas at the inlet to a turbine wheel in a turbine in which a compressor fuels air into a chamber where it is heated and the heated products exiting the chamber form the propulsion gas. The temperature of the heated products exiting the chamber is a function of the inlet static and total pressure, the total inlet temperature, the static pressure of the heated products and the static pressure drop across the chamber.

Claims

1. Apparatus for monitoring the temperature of the propulsion gas at the inlet to a turbine wheel in a turbine in which a compressor feeds air into a chamber where it is heated and the products exiting the chamber form the propulsion gas, comprising in combination;

first means responsive to the static pressure of air fed into said chamber;

second means responsive to the total temperature of the air fed into said chamber;

third means responsive to the total pressure of the air fed to said chamber;

fourth means responsive to the static pressure of the chamber products, and

fifth means responsive to said first through fourth means for indicating the temperature of the gas exiting said chamber as a function of a static pressure drop across said chamber.

2. An apparatus according to claim 1 wherein said compressor feeds air into said chamber where it is mixed with a fuel and the air/fuel combustion products exiting the chamber form the propulsion gas.

3. An apparatus according to claim 1 wherein the temperature of the propulsion gas is calculated by multiplying the inlet temperature by a temperature rise ratio wherein the temperature rise ratio T_O4 lT₀₃ is given by ##EQU2## wherein:

T₀ =Total temperature, i.e. static temperature plus the temperature equivalent of the velocity head.

P₀ =Total pressure

P=Static pressure

λ

=Specific heat ratio, i.e., 1.4 for air and 1.3 for combustion gases

Sub 3=Combustion chamber inlet

Sub 4=Combustion chamber outlet.

4. Apparatus for monitoring the temperature of the propulsion gas at the inlet to a turbine wheel in a gas turbine in which a compressor feeds air into a combustion chamber where it is mixed with a fuel and the air/fuel combustion products exiting the chamber form the propulsion gas, comprising in combination;

a flow tube having two ends and a flow restriction intermediate said ends;

means mounting one end of said flow tube so that it is responsive to the static pressure of the compressed air entering said combustion chamber;

means mounting the other end of said flow tube so that it is responsive to the static pressure of the combustion products exiting said chamber;

means for measuring a pressure drop across said restriction;

means for measuring total temperature of air entering said combustion chamber;

means for combining pressure measurements into a combustion chamber temperature rise ratio and then multiplying by the inlet temperature to obtain the temperature of the propulsion gas.

5. An apparatus according to claim 4 wherein the temperature rise ratio T₀₄ / T₀₅ is given by:

##EQU3## wherein;

T₀ =Total temperature, i.e. static temperature plus the temperature equivalent of the velocity head.

P₀ =Total pressure

P=Static pressure

λ

=Specific heat ratio, i.e., 1.4 for air and 1.3 for combustion gases Sub 3=Combustion chamber inlet Sub 4=Combustion chamber outlet,