US 12,291,979 B1
Turbine engine and turbine nozzle
Paul Hadley Vitt, Liberty Township, OH (US); Jeffrey Donald Clements, Mason, OH (US); Brian Keith Kestner, Cincinnati, OH (US); and Shai Birmaher, Cincinnati, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by GENERAL ELECTRIC COMPANY, Cincinnati, OH (US)
Filed on Jun. 28, 2024, as Appl. No. 18/757,786.
Application 18/757,786 is a continuation of application No. 18/494,933, filed on Oct. 26, 2023.
Int. Cl. F01D 9/04 (2006.01)
CPC F01D 9/04 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/128 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a core including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, the core defining an engine centerline;
the compressor section including a set of compressor stages, the set of compressor stages including a first compressor stage and a last compressor stage, each of the set of compressor stages comprising a pair of non-rotating vanes and rotating blades, wherein an overall pressure ratio (OPR) defined as a ratio of a total pressure immediately downstream of the last compressor stage to a total pressure immediately upstream of an inlet of the fan section, wherein the OPR is in a range of 20-60;
the turbine section including a set of turbine stages having a number of turbine stages (N) in a range of 1-2, each turbine stage comprising pairs of non-rotating vanes and rotating blades, wherein a set of vanes defines a nozzle, and wherein a first stage turbine nozzle is closest to the combustion section;
wherein the first stage turbine nozzle has a solidity (σ) defined as a ratio of a representative axial chord length for the first stage turbine nozzle to a representative circumferential spacing between adjacent vanes of the first stage turbine nozzle, wherein the solidity is in a range of 0.2-0.8;
wherein the turbine engine has a Nox Dp/Foo ratio (DPFR) defined as a ratio of a Nox Dp/Foo of a predecessor turbine engine to a Nox Dp/Foo of the turbine engine, wherein the DPFR is in a range of 0.8-2.0;
wherein the turbine section and compressor section define a core radius ratio (CRR), the CRR defined as a ratio of Rt/Rc, where Rt is a radius defined by the first turbine stage and Rc is a radius defined by the last compressor stage, wherein the CRR is in a range of 0.9-1.3; and
wherein the first stage turbine nozzle having a durability and performance index (DPI) defined as:

OG Complex Work Unit Math
wherein the DPI is in the range of 1.001-2.201.